Technical Description Template

TECHNICAL DESCRIPTION
MD 500E
MD 530F
MD 520N
00
Marketing and Sales
4555 E. McDowell Road
Mesa, Arizona 85215-9734
Comments and/or questions may be directed to:
Sales: (480) 346-6344
Fax: (480) 346-6339
E-mail: sales@mdhelicopters.com
Revised
January 2011
© 2011 MD Helicopters, Inc. All rights reserved.
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 helicopters which may be considered necessary.
TABLE OF CONTENTS
TABLE OF CONTENTS
1.0
MD 500E® FEATURES AND BENEFITS………………………………..………………………...
1.1
Dimensions………………………..…...............................................................................
page
1
2
2.0
MD 500E® STANDARD EQUIPMENT…………………………………………………………….…
3-5
3.0
MD 500E® PERFORMANCE SPECIFICATIONS…………………………………………….........
3.1
Performance Specifications (C20B Engine)………………………..…..............................
3.2
Performance Specifications (C20R Engine)………………………..…..............................
3.3
Hover-In-Ground-Effect (C20B Engine)…………………………………..………...............
3.4
Hover-Out-of-Ground-Effect (C20B Engine)………………..…………………………........
3.5
Takeoff Gross Weight Worksheet (C20B Engine)……………….……………..................
3.6
Payload vs. Range (5000’, ISA) (C20B Engine)…………..………………………………..
3.7
Speed for Best Range (C20B Engine)…………..…………………………………………..
3.8
Speed for Best Endurance (C20B Engine)…………..……………………………………..
3.9
Fuel Flow, Sea Level, ISA (15ºC) (C20B Engine)…………..……………………………..
3.10
Fuel Flow, Sea Level, ISA + 20ºC (35ºC) (C20B Engine)…………..…………………….
3.11
Fuel Flow, 4000 feet, ISA (7ºC) (C20B Engine)…………..………………………………..
3.12
Fuel Flow, 4000 feet, ISA + 20ºC (27ºC) (C20B Engine)…………..……………………..
3.13
Hover-In-Ground-Effect (C20R Engine)…………..…………………………………………
3.14
Hover-Out-of-Ground-Effect (C20R Engine)…………..……………………………………
3.15
Takeoff Gross Weight Worksheet (C20R Engine)…………..……………………………..
3.16
Payload vs. Range (5000’, ISA) (C20R Engine)…………..………………………………..
3.17
Speed for Best Range (C20R Engine)……………………………………………………....
3.18
Speed for Best Endurance (C20R Engine)…………..………………………………….....
3.19
Fuel Flow, Sea Level, ISA (15ºC) (C20R Engine)…………..……………..……………….
3.20
Fuel Flow, Sea Level, ISA + 20ºC (35ºC) (C20R Engine)………….……………………..
3.21
Fuel Flow, 4000 feet, ISA (7ºC) (C20R Engine)…………..………………………………..
3.22
Fuel Flow, 4000 feet, ISA + 20ºC (27ºC) (C20R Engine)…………..……………………..
0
MD 500E® DIRECT OPERATING COST ESTIMATES…………..…………………………….....
4.1
MD 500E® Direct Operating Cost Worksheet……………………….....………..…..........
6-27
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
5.0
MD 500E® COMPONENT MAINTENANCE SCHEDULE…………………………………………
30
6.0
MD 530F® FEATURES AND BENEFITS……………..……………………………………………..
6.1
Dimensions…………………….……………………………..…..........................................
31
32
7.0
MD 530F® STANDARD EQUIPMENT…………………………..…………………………………..
33-35
8.0
MD 530F® PERFORMANCE SPECIFICATIONS…………………………………………………..
8.1
Hover-In-Ground Effect……….……………………………..…..........................................
8.2
Hover-Out-of-Ground Effect………………………..………………....................................
8.3
Takeoff Gross Weight Worksheet…………………………………..………........................
8.4
Payload vs. Range (5000’, ISA)….………………………………..….................................
8.5
Speed for Best Range…………………….…………………...............................…………
8.6
Speed for Best Endurance………………………………..………......................................
8.7
Fuel Flow, Sea Level, ISA (15˚C)….………………………………..…..............................
8.8
Fuel Flow, Sea Level, ISA + 20˚C (35˚C).…………..………………….............................
8.9
Fuel Flow, 4,000 feet, ISA (7˚C)…………..…………………............................................
8.10
Fuel Flow, 4,000 feet, ISA + 20˚C (27˚C)…………………………………..………............
36-46
37
38
39
40
41
42
43
44
45
4.0
28
29
46
TABLE OF CONTENTS
9.0
0MD 530F® DIRECT OPERATING COST
ESTIMATES…………………………………………….
9.1
MD 530F® Direct Operating Cost Worksheet…………………..…………….................
page
47
48
10.0
MD 530F® COMPONENT MAINTENANCE SCHEDULE.………………………………………...
49
11.0
MD 520N® SYSTEM DESCRIPTION……………………………………………………………..….
11.1
MD 520N® Design Description…………..…...................................................................
11.1.1--- MD 520N® Outside Dimensions………..…………………...........................…..
11.1.2--- MD 520N® Inboard Profile and Features…………………………..……............
11.2
MD 520N® On Patrol……….……………………………..…............................................
11.2.1---Maintenance made easy……………….…………..............................……….….
11.2.2---Interchangeability…………..……………………..……........................................
11.3
NOTAR® Anti-Torque System…….………………………………..…...............................
11.3.1---Description of the NOTAR® System……..….…….............................................
11.3.2---NOTAR® System Components…………..…………………................................
11.3.3---Reduced Aircraft Vibration…………………..……………..……….......................
11.3.4---Low External Noise……..…………………..............................……………..…....
11.3.5---Inherent Safety…………..……………..…..........................................................
11.3.6---Improved Handling…………………………………..…….....................................
50-60
51
51
53
54
55
56
57
57
57
58
59
60
60
12.0
MD 520N® STANDARD EQUIPMENT……………………………………………………………....
61-63
13.0
MD 520N® PERFORMANCE SPECIFICATIONS…………………………………………………..
13.1
Hover-In-Ground Effect……….……………………………..…..........................................
13.2
Hover-Out-of-Ground Effect………………………..………………....................................
13.3
Takeoff Gross Weight Worksheet…………………………………..………........................
13.4
Payload vs. Range (5000’, ISA)….………………………………..….................................
13.5
Speed for Best Range…………………..…………………..................................…………
13.6
Speed for Best Endurance…………………………………..………..................................
13.7
Fuel Flow, Sea Level, ISA (15˚C)….………………………………..…..............................
13.8
Fuel Flow, Sea Level, ISA + 20˚C (35˚C)…………..…………………..............................
13.9
Fuel Flow, 4,000 feet, ISA (7˚C)…………..…………………............................................
13.10 Fuel Flow, 4,000 feet, ISA + 20˚C (27˚C)...…………………………………..……….........
64-74
65
66
67
68
69
70
71
72
73
74
14.0
MD 520N® DIRECT OPEARTING COST ESTIMATES......………………………………………..
14.1
MD 520N Direct Operating Cost per Hour Worksheet………………...............................
75
76
15.0
COMPONENT MAINTENANCE SCHEDULE……………...........................................................
77
16.0
MD500 SERIES OPTIONAL EQUIPMENT…………………………………………………….…….
78-81
17.0
PRODUCT SUPPORT PLAN…………………………………………………………………….……
82-84
18.0
TRAINING…………………………………………………………………………………………….….
85-86
FEATURES AND BENEFITS
1.0 MD500E® Features and Benefits
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 Rolls-Royce 250-C20B or 450-shp
Rolls-Royce 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 applications; air rescue operations; and
numerous other tasks within the construction, petroleum and forestry industries.
Standard high-clearance skids permit operations in rough terrain, while other optional
equipment, such as inflatable floats and litter kit increase the versatility of the MD 500E®.
Proven reliability of the de-rated turbine engine, fail-safe design and a worldwide network of
factory-authorized service centers assure customer satisfaction.
ƒ STANDARD COCKPIT INTERIOR
ƒ STANDARD CABIN INTERIOR
1
DIMENSIONS
1.1
Dimensions
2
STANDARD EQUIPMENT
2.0 MD 500E® Standard Equipment
Airframe
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Extended Landing Gear
Rapid Door Removal Hinges (cockpit and cabin)
Tinted Canopy Panels
Tinted Door/window panel-left front
Tinted Door/window panel-left rear
Tinted Door/window panel-right front
Tinted Door/window panel-right rear
Rain Gutter Set
Keyed Locks (4)
Fuselage Hard Points
Jacking Fittings
Passenger Steps
Anti-collision Lights (2)
Landing Light, nose mounted
Position Lights
Interior
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LH Rotor Brake
Heater Defogger System
Crew Seats with 4-point Harness Restraint
Passenger Seats with 3-point Harness Restraint
Vinyl and Fabric Cushions
Vinyl Interior Trim Panels
Crew and Cabin Compartment Floor Carpet
Map Case
Fire Extinguisher
First-Aid Kit
Cabin 28-volt Utility Outlet
Battery-Heavy Duty Marathon 17-ampere-hour
Fresh Air Ventilation System
Cockpit Utility Light
Cabin Convenience Light
Instrument Lighting
Cabin Soundproofing
Cargo Tie-Down Fittings
Rotor and Controls
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Dual LH Command Flight Controls
3
STANDARD EQUIPMENT
Engine and Electrical
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Rolls-Royce 250-C20B Engine, 420 shp (313 kw)
Automatic Engine Reignition
Engine Wash Kit, MD 500 series
64 Gallon (242 l) Fuel System
85 amp Starter Generator
External Power Receptacle
Engine anti-ice
Flight and Engine Instruments
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AFS Engine Inlet Barrier Filter
Facet Oil Filter
Dual tachometer, NR and N2
Engine oil pressure indicator
Engine torque meter
N1 tachometer
Fuel quantity indicator
Digital chronometer
Airspeed indicator
Barometric altimeter
DC ammeter
Outside air temperature indicator
Magnetic compass
Turbine outlet temp indicator
Engine oil temp indicator
4
STANDARD EQUIPMENT
Annuciator Panel
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Battery Overtemp Warning Light
Engine Chip Detector Warning Light
Engine Out Warning Light
Fuel Filter Obstruction Warning Light
Fuel Low Warning Light
Generator Out Warning Light
Low Rotor rpm Warning Light
Main Transmission Chip Detector Warning Light
Main Transmission Oil Pressure Warning Light
Main Transmission Oil Temp Warning Light
Tail Rotor Transmission Chip Detector Warning Light
Miscellaneous
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Engine and Airframe Log Books
Engine Maintenance Manual
Battery Logbook
Flight Manual
Handbook of Maintenance Instructions
Illustrated Parts Catalog
Engine Exhaust Cover
Engine Inlet Cover
Pitot Tube Cover
Fan Inlet Cover
Main Rotor Blade Tie-Downs
Ground Handling Wheels
One color paint
5
PERFORMANCE SPECIFICATIONS
3.0 MD500E® PERFORMANCE SPECIFICATIONS
3.1
Performance Specifications (C20B Engine)
Performance With C20B Engine
Characteristics at Design Gross Weight
Metric
1361 KG
Imperial
3000 lb.
Maximum Cruise Speed
Sea level
1524 m (5,000 ft)
249 km/hr
246 km/hr
135 kt (155 mph)
133 kt (153 mph)
Speed for Best Range
1524 m (5,000 ft)
222 km/hr
120 kt (138 mph)
Maximum Permitted Speed
VNE at sea level
282 km/hr
152 kt (175 mph)
Maximum Range
Sea level
1524 m (5,000 ft)
478 km
537 km
258 nm (297 mi)
290 nm (304 mi)
Maximum Endurance
Sea level
2.8 hr
2.8 hr
Maximum Rate of Climb:(TOP)
Sea level, Standard
day
ISA +20° C day
9.0 m/sec
1,770 fpm
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
907 kg
2,000 lb
Maximum Hook Capacity
Hovering Performance
In-ground effect
Standard day
ISA + 20° C day
2591 m
1829 m
8,500 ft
6,000 ft
Out-of-ground effect:
Standard day
ISA + 20° C day
1829 m
945 m
6,800 ft
3,100 ft
Metric
Imperial
1361 kg
3,000 lb
1610 kg
3,550 lb
WEIGHTS
Characteristics
Maximum Gross Weight
Normal category
External load operations
Empty Weight
Standard configuration
672 kg
1,481 lb
Useful Load
Normal category
689 kg
1,519 lb
938 kg
2,069 lb
183 kg
403 lb
Metric
Imperial
External load operations
Usable Fuel Capacity
242 L (64 gal
POWER PLANT
Characteristics
Rolls-Royce Model 250-C20B gas
turbine
Rated power:
313 kw
420 shp
Derated for reliability and safety to
Takeoff power
Max continuous power
280 kw
261 kw
375 shp
350 shp
6
PERFORMANCE SPECIFICATIONS
3.2
Performance Specifications (C20R Engine)
Performance with C20R Engine
Characteristics at Design Gross Weight
Metric
1361 KG
Imperial
3000 lb.
Maximum Cruise Speed
Sea level
1524 m (5,000 ft)
249 km/hr
251 km/hr
135 kt (155 mph)
136 kt (156 mph)
Speed for Best Range
1524 m (5,000 ft)
222 km/hr
120 kt (138 mph)
Maximum Permitted Speed
VNE at sea level
282 km/hr
152 kt (175 mph)
Maximum Range
Sea level
1524 m (5,000 ft)
472 km
532 km
255 nm (293 mi)
287 nm (297 mi)
Maximum Endurance
Sea level
2.7 hr
2.7 hr
Maximum Rate of Climb:(TOP)
Sea level, Standard day
ISA +20° C day
9.0 m/sec
9.0 m/sec
1,770 fpm
1,776 fpm
Maximum Operating Altitude
Density Altitude
4877 m
16,000 ft
Service Ceiling
ISA
5029 m
16,500 ft
907 kg
2,000 lb
Maximum Hook Capacity
Hovering Performance
In-ground effect
Standard day
ISA + 20° C day
3444 m
2103 m
11,300 ft
6,900 ft
Out-of-ground effect:
Standard day
ISA + 20° C day
2652 m
1250 m
9,500 ft
4,100 ft
WEIGHTS
Characteristics
Metric
Imperial
Maximum Gross Weight
Normal category
1361 kg
External load operations 1610 kg
3,000 lb
3,550 lb
Empty Weight
Standard configuration
686 kg
1,517 lb
Useful Load
Normal category
673 kg
External load operations 922 kg
1,483 lb
2.033 lb
Usable Fuel Capacity
242 L (64 gal)
403 lb
183 kg
POWER PLANT
Characteristics
Metric
Imperial
Rolls-Royce Model 250-C20B gas
turbine, Rated power
336 kw
450 shp
280 kw
261 kw
375 shp
350 shp
De-rated for reliability and safety to
Takeoff power:
Max. continuous power
7
PERFORMANCE SPECIFICATIONS
3.3
Hover-In-Ground-Effect (C20B Engine)
THIS CHART BASED ON CABIN HEAT, ENGINE ANTI-ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO
PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET
REDUCE WEIGHT:
1. 55LB WITH SCAVENGE ON
2. 40LB WITH MIST ELIMINATOR INSTALLED
16000
-2
5
14000
-5
o
5
o
-1
5
o
C
o
OAT
15
OAT oC
WTD
-5
1
15
2
35
3
NOT VERIFIED WHEN MAIN ROTOR
BLADES HAVING ABRASION STRIPS
ARE INSTALLED
o
o
10000
8000
o
20
A+
IS
PRESSURE ALTITUDE - FEET
C
A
IS
o
12000
45
o
INCREASE (OR DECREASE) WT.
CAPABILITY LBS (ABOVE CRITICAL
ALTITUDE) PER 10 AMP REDUCTION (OR
INCREASE) IN ELECTRICAL LOAD
o
25
35
INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN
ROTOR BLADES ONLY
DECREASE WEIGHT: 50LB WITH ABRASION STRIPS ON TAIL
ROTOR BLADES ONLY
C
6000
4000
REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS:
(APPLICABLE TO ALL TEMPERATURES)
2000
PRESSURE
ALT. FT.
CABIN
HEAT
ANTIICE
BOTH
SL TO 4000
8000
12000
16000
220
152
111
86
232
157
117
89
469
306
227
172
0
2200
2400
2600
2800
3000
3200
3400
3600
GROSS WEIGHT - POUNDS
<<<< ROLLS ROYCE 250-C20B >>>>
8
F03-036-1
PERFORMANCE SPECIFICATIONS
3.4
Hover-Out-of-Ground-Effect (C20B Engine),
9
PERFORMANCE SPECIFICATIONS
3.5
Takeoff Gross Weight Worksheet (C20B Engine)
C20B
Mission #1
1,481 lb
Empty Weight
(672 kg)
170 lb
Pilot
(77 kg)
403 lb
Fuel
(183 kg)
946 lb
Payload
(428 kg)
3,000 lb
Takeoff GW
(1361 kg)
10
Mission #2
PERFORMANCE SPECIFICATIONS
3.6
Payload vs Range (5000’, ISA) (C20B Engine)
11
PERFORMANCE SPECIFICATIONS
3.7
Speed for Best Range (C20B Engine)
12
PERFORMANCE SPECIFICATIONS
3.8
Speed for Best Endurance (C20B Engine)
13
PERFORMANCE SPECIFICATIONS
3.9
Fuel Flow, Sea Level, ISA (15°C) (C20B Engine)
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
PERFORMANCE SPECIFICATIONS
3.10 Fuel Flow, Sea Level, ISA +20°C (35°C) (C20B Engine)
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
PERFORMANCE SPECIFICATIONS
3.11 Fuel Flow, 4,000 feet, ISA (7°C) (C20B Engine)
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
PERFORMANCE SPECIFICATIONS
3.12 Fuel Flow, 4,000 feet, ISA +20°C (27°C) (C20B Engine)
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
PERFORMANCE SPECIFICATIONS
3.13 Hover-In-Ground-Effect (C20R Engine)
18
PERFORMANCE SPECIFICATIONS
3.14 Hover-Out of-Ground-Effect (C20R Engine)
19
PERFORMANCE SPECIFICATIONS
3.15 Takeoff Gross Weight Worksheet (C20R Engine)
C20R
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)
Mission #1
20
Mission #2
PERFORMANCE SPECIFICATIONS
3.16 Payload vs Range (5000’, ISA) (C20R Engine)
21
PERFORMANCE SPECIFICATIONS
3.17 Speed for Best Range (C20R Engine)
22
PERFORMANCE SPECIFICATIONS
3.18 Speed for Best Endurance (C20R Engine)
23
PERFORMANCE SPECIFICATIONS
3.19 Fuel Flow, Sea Level, ISA (15°C) (C20R Engine)
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
PERFORMANCE SPECIFICATIONS
3.20 Fuel Flow, Sea Level, ISA +20°C (35°C) (C20R Engine)
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
PERFORMANCE SPECIFICATIONS
3.21 Fuel Flow, 4,000 feet, ISA (7°C) (C20R Engine)
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
PERFORMANCE SPECIFICATIONS
3.22 Fuel Flow, 4,000 feet, ISA +20°C (27°C) (C20R Engine)
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
DIRECT OPERATING COST ESTIMATES
4.0 MD 500E® Estimated Direct Operating Cost Per Hour (Based upon year 2010 US$)
C20B
Engine
C20R+
Engine
$ 106.11
$ 3.18
$ 113.97
$ 3.42
Fuel and Lubricants 1:
Fuel @ $3.93* gallon @ approx. 27 gallons per hour.
Lubricants @ 3% of fuel
Total Fuel ..................................................................................
$ 109.29
$ 117.39
Airframe Maintenance and Spares2:
Maintenance labor costs:
Scheduled (.15 Manhours/Flight Hours) @ $75.00/Hour*
Unscheduled (.26 Manhours/Flight Hours) @ $75.00/Hour*
Spares Cost:
Scheduled (Inspection) Parts: Used during periodic
inspection i.e. filters, seals, o-rings, etc.....................................
On-Condition/Unscheduled Part................................................
Reserves: Component Overhaul (TBO) ....................................
Reserves: Limited-Life Parts ...................................................
Total Airframe Cost ...................................................................
$ 11.25
$ 19.50
$ 30.75
$ 11.25
$ 19.50
$ 30.75
$ 5.78
$ 21.12
$ 45.52
$ 42.72
$ 5.78
$ 20.11
$ 45.52
$ 42.72
$ 115.14
$ 115.14
Engine3:
Scheduled maintenance labor and parts..........................
Reserve for engine overhaul, spares and
accessories.......................................................................
Total Engine ..............................................................
Total Direct Operating Cost4 ........................................
$ 3.00
$ 3.00
$ 70.19
$73.20
$ 73.69
$ 328.87
$ 75.20
$ 338.48
1 Fuel cost and labor rate* is based on U.S. Average
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
2 Overhaul costs are based on participation in factory exchange program
3 Engine fleet maintenance costs provided by Rolls-Royce Engine Company
4 Indirect costs such as insurance, hangar, salary, etc., are excluded
Cost figures shown are extrapolated from a broad database and are intended for example
purposes only. Actual costs will vary, depending on local operating condition, pricing and supplier
practices. We encourage you top compare these figures with other manufacturers, using the
same unit costs for fuel, labor, etc.
28
DIRECT OPERATING COST ESTIMATES
4.1 MD 500E® Direct Operating Cost Worksheet Fuel and Lubricants
„ Fuel and Lubricants
Fuel @ $ per gallon @ approx. gallons per hour………………………………………
$_________
Lubricants @ ______ % of fuel ………………………………………………………....
$_________
Total Fuel and Lubricants Cost………………………………………………………..
$_________(A)
„ 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 Maintenance and Spares Cost……………………………………...
$_________(B)
„ 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 OPERATING COST (A+B+C) ………………………………….
$_________(D)
FIXED OPERATING COST FIXED OPERATING COST
„ Depreciation
Hull insurance ……………………………………………………………………………..
$_________
Liability insurance …………………………………………………………………………
$_________
Pilot salary …………………………………………………………………………………
$_________
Hangar rental …………………………………………………………..………………….
$_________
Total Annual Fixed Operating Cost …………………………………….……………
Total Hours ( _____________ ) flown annually (F) ………………………….……….
$_________(E)
$_________(F)
TOTAL FIXED OPERATING COST PER HOUR (E+F) ………………………….….
$_________(G)
Total Direct Operating Cost Per Hour (from above) ………………….…..………..
$_________(D)
TOTAL HOURLY FIXED OPERATING COST (D+G)………………………………...
$_________
29
COMPONENT MAINTENANCE SCHEDULE
5.0 Component Maintenance Schedule
Overhaul Systems
Limited-Life Parts
Component
Finite Time (hr)
Component
Finite Time (hr)
Main Rotor Blade
3,530
Transmission/MR
5,000
Blade Pin
7,600
M/R Swashplate
2,770
Main Rotor Hub
8,900
M/R Hub
2,770
Pitch Housing/MR
9,100
Overrunning Clutch
1,800
Retention Strap/MR
2.770
T/R Transmission
4,800
Starter, Generator
1,200
Bolt-Lead Lag/Mr
6,120
Blower Bearings
1,200
Lead Lag Link/MR
11,080
Blower Belt
1,200
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
30
FEATURES AND BENEFITS
6.0 MD 530F® Features and Benefits
The MD 530F® is engineered to meet your requirements for hot-day, high-altitude operation.
Equipped with the 650 shp Rolls-Royce 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. 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 high altitude lift capability of the MD 530F® 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 the most versatile MD helicopter. The T-shaped instrument panel provides
space for a full complement of avionics.
Rear seat passengers have increased headroom and visibility. 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). Standard high-clearance
skids permit operation in rough terrain, while other optional equipment, such as inflatable floats
and litter kit increase the versatility of the MD 530F®.
Proven reliability, fail-safe design and the worldwide network of factory-authorized service
centers assure customer satisfaction.
ƒ STANDARD COCKPIT INTERIOR
ƒ STANDARD CABIN INTERIOR
31
DIMENSIONS
6.1
Dimensions
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.
32
STANDARD EQUIPMENT
7.0 MD 530F® Standard Equipment
*Required Options Included in Base Price as of 2008
Airframe
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
Extended Landing Gear
Rapid Door Removal Hinges (cockpit and cabin)
Tinted Canopy Panels
Tinted Door/window panel-left front
Tinted Door/window panel-left rear
Tinted Door/window panel-right front
Tinted Door/window panel-right rear
Rain Gutter Set
Keyed Locks (4)
Fuselage Hard Points
Jacking Fittings
Passenger Steps
Anti-Collision Lights (2)
Landing Light, nose mounted
Position Lights
Interior
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
LH Rotor Brake
Heater Defogger System
Crew Seats with 4-point Harness Restraint
Passenger Seats with 3-point Harness Restraint
Vinyl and Fabric Cushions
Vinyl Interior Trim Panels
Crew and Cabin Compartment Floor Carpet
Map Case
Fire Extinguisher
First-Aid Kit
Cabin 28-volt Utility Outlet
Battery-Heavy Duty Marathon 17-ampere-hr
Fresh Air Ventilation System
Cockpit Utility Light
Instrument Lighting
Cabin Soundproofing
Cargo Tie-Down Fittings
Cabin Convenience Light
Rotors and Controls
ƒ
Dual LH Command Flight Controls
33
STANDARD EQUIPMENT
Engine and Electrical
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
Rolls-Royce 250-C30 Engine, 650 shp (485 kw)
Automatic Engine Reignition
Engine Wash Kit, MD 500 series
64 Gallon (242 L) Fuel System 85 amp Starter Generator
200 amp Starter Generator
External Power Receptacle
Engine Anti-Ice
Flight and Engine Instruments
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
AFS Engine Inlet Barrier Filter
Facet Oil Filter
Dual Tachometer, NR and N2
Engine Oil Pressure Indicator
Engine Torque Meter
Engine Oil Temp Indicator
N1 Tachometer
Fuel Quantity Indicator
Digital Chronometer
Airspeed Indicator
Barometric Altimeter
DC Ammeter
Outside Air Temperature Indicator
Magnetic Compass
Turbine Outlet Temp Indicator
34
STANDARD EQUIPMENT
Annuciator Panel
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
Battery Overtemp Warning Light
Engine Chip Detector Warning Light
Engine Out Warning Light
Fuel Filter Obstruction Warning Light
Fuel Low Warning Light
Generator Out Warning Light
Low Rotor rpm Warning Light
Main Transmission Chip Detector Warning Light
Main Transmission Oil Pressure Warning Light
Main Transmission Oil Temperature Warning Light
Tail Rotor Transmission Chip Detector Warning Light
Miscellaneous
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
Ground handling wheels
Engine and airframe log books
Engine maintenance manual
Battery logbook
Flight manual
Handbook of maintenance instructions
Illustrated parts catalog
Engine exhaust cover
Engine inlet cover
Pitot Tube Cover
Main Rotor Blade Tie-Downs
One color paint
35
PERFORMANCE SPECIFICATIONS
8.0 Performance Specifications
Characteristics at
Design Gross Weight
Metric
1406 kg
Imperial
3,100 lb
Maximum Cruise Speed
Sea Level
1524 m (5,000 ft)
248 km/hr
249 km/hr
134 kt (154 mph)
135 kt (155 mph)
Speed for Best Range
1524 m (5,000 ft)
243 km/hr
118 kt (219 mph)
Maximum Permitted
Speed
VNE at sea level
282 km/hr
152 kt (175 mph)
Maximum Range
Sea Level
1524 m (5,000 ft)
2.2 hrs
430 km
2.2 hrs (237 m)
232 nm (267 m)
Maximum Endurance
Sea Level
381 km
206 nm (237 m)
Maximum Rate of Climb
Sea Level, Standard Day
ISA +20° C Day
10.5 m/sec
105 m/sec
2069 fpm
2061 fpm
Maximum Operating
Altitude
Density Altitude
6096 m
20,000 ft
Service Ceiling
ISA
5700 m
18,700 ft
907 kg
2,000 lb
Maximum Hook
Capacity
Hovering Performance (No wind)
In-ground effect
Standard Day
ISA +20° C Day
4877 m
4359 m
16,000 ft
14,300 ft
Out-of-ground effect
Standard Day
ISA +20° C Day
4389 m
3536 m
14,400 ft
11,600 ft
Metric
Imperial
WEIGHTS
Characteristics
Maximum Gross Weight
Normal Capacity
External Load Operations
1406 kg
1701 kg
3,100 lb
3,750 lb
Empty Weight
Standard Configuration
722 kg
1,591 lb
Useful Load
Normal Capacity
684 kg
1,509 lb
979 kg
2,159 lb
183 kg
403 lb
Metric
Imperial
External Load
Operations
Usable Fuel Capacity
242 l (64 gal)
POWER PLANT
Characteristics
Rolls-Royce 250-C30
gas turbine
Rated Power
485 kw
650 shp
Derated for reliability
and safety to
Takeoff Power
Max Continuous Power
317 kw
280 kw
425 shp
375 shp
36
PERFORMANCE SPECIFICATIONS
8.1
Hover-In-Ground-Effect
37
PERFORMANCE SPECIFICATIONS
8.2
Hover-Out of-Ground-Effect
38
PERFORMANCE SPECIFICATIONS
8.3 Takeoff Gross Weight Worksheet
Empty Weight
Example
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)
Mission #1
39
Mission #2
PERFORMANCE SPECIFICATIONS
8.4
Payload vs Range (5000’, ISA)
40
PERFORMANCE SPECIFICATIONS
8.5 Speed for Best Range
41
PERFORMANCE SPECIFICATIONS
8.6
Speed for Best Endurance
42
PERFORMANCE SPECIFICATIONS
8.7
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.
43
PERFORMANCE SPECIFICATIONS
8.8 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.
44
PERFORMANCE SPECIFICATIONS
8.9
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.
45
PERFORMANCE SPECIFICATIONS
8.10 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.
46
DIRECT OPERATING COST ESTIMATES
9.0 MD 530F® Estimated Direct Operating Cost Per Hour (Based upon year 2010US)
C30
Engine
Fuel and Lubricants 1:
Fuel @ $3.93* per gallon @ approx. 35 gallons per hour. ............................
Lubricants @ 3% of fuel ................................................................................
Total Fuel .....................................................................................................
Airframe Maintenance and Spares2:
Maintenance labor costs:
Scheduled (.15 Manhours/Flight Hours) @ $75.00/Hour*.............................
Unscheduled (.26 Manhours/Flight Hours) @ $75.00/Hour*.........................
Spares Cost:
Scheduled (Inspection) Parts: Used during periodic inspection i.e. filters,
seals, o-rings, etc ..........................................................................................
On-Condition/Unscheduled Part ...................................................................
Reserves: Component Overhaul (TBO)........................................................
Reserves: Limited-Life Parts ........................................................................
Total Airframe Cost ......................................................................................
Engine3:
Scheduled maintenance labor and parts...............................................
Reserve for engine overhaul, spares and
accessories ...........................................................................................
Total Engine ......................................................................................................
Total Direct Operating Cost4 ...........................................................................
1
$ 137.55
$ 4.13
$ 141.68
$ 11.25
$ 19.50
$ 30.75
$ 5.78
$ 21.12
$ 46.93
$ 48.92
$ 122.75
$ 3.00
$ 70.91
$ 73.91
$ 369.09
Fuel cost and labor rate* is based on U.S. Average
Average cost while operating under the following conditions:
Gross Weight: 10% less than maximum certified
Speed: Maximum Range Speed, 124 KIAS
Altitude: 1,000 feet on a standard day
2
Overhaul costs are based on participation in factory exchange program
3
Engine fleet maintenance costs provided by Rolls-Royce Engine Company
4
Indirect costs such as insurance, hangar, salary, etc., are excluded
Cost figures shown are extrapolated from a broad database and are intended for example purposes only.
Actual costs will vary, depending on local operating condition, pricing and supplier practices. We encourage
you top compare these figures with other manufacturers, using the same unit costs for fuel, labor, etc.
47
DIRECT OPERATING COST ESTIMATES
9.1 MD 530F® Direct Operating Cost Worksheet
„ Fuel and Lubricants
Fuel @ $ per gallon @ approx. gallons per hour……………………………………..
$_________
Lubricants @ ______ % of fuel ………………………………………………………...
$_________
Total Fuel and Lubricants Cost………………………………………………………
$_________(A)
„ 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 Maintenance and Spares Cost…………………………………….
$_________(B)
„ 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 OPERATING COST (A+B+C) ………………………………..
$_________(D)
FIXED OPERATING COST
„ Depreciation
Hull insurance ……………………………………………………………………………
$_________
Liability insurance ……………………………………………………………………….
$_________
Pilot salary ……………………………………………………………………………….
$_________
Hangar rental …………………………………………………………..………………..
$_________
Total Annual Fixed Operating Cost …………………………………….…………..
Total Hours ( ______________ ) flown annually (F) ………………………….……..
$_________(E)
$_________(F)
TOTAL FIXED OPERATING COST PER HOUR (E+F) ………………………….…
$_________(G)
Total Direct Operating Cost Per Hour (from above) ………………….…..………
$_________(D)
TOTAL HOURLY FIXED OPERATING COST (D+G)……………………………….
$_________
48
COMPONENT MAINTENANCE SCHEDULE
10.0
Component Maintenance Schedule
Limited-Life Parts
Component
Overhaul Systems
Finite Time (hr)
Component
Finite Time (hr)
Main Rotor Blade
3,430
Main Rotor Transmission
5,000
Blade Pin
7,600
Main Rotor Swashplate
2,770
Main Rotor Hub
8,900
Main Rotor Hub
2,770
Pitch Housing/MR
9,100
Overrunning Clutch
1,800
Retention Strap/MR
2,770
T/R Transmission
3,365
Bolt-Lead Lag/MR
6,120
Starter Generator
1,200
Lead Lag Link/MR
11,080
Blower Bearings
1,200
Drive Shaft
3,675
Blower Belt
1,200
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
49
SYSTEM DESCRIPTION
11.0
MD 520N® SYSTEM DESCRIPTION
Airborne Law Enforcement Configuration
Fast:
Vne of 175 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
2,264 pounds (1027 kg) external
HOGE at 6,000 ft (1829 m) @ISA HIGE at 11,200 ft (3414 m) @ISA
ROC of 1,775 feet per minute (9.0 m/s)
Versatile:
20,000 foot (6096 m) Maximum Operating Altitude
Operating temperature range of -40˚C to +52˚C
15 degree slope landing
Safety:
Environment:
Elimination of tail rotor hazards
Quiet operations – Flyover at 500 feet AGL = 72.5 dbA
50
SYSTEM DESCRIPTION
11.1
MD 520N® Design Description
The MD 520N® is a fast, agile, lightweight, turbine powered, all-purpose helicopter. Advanced
technology has been used in the design and construction of the aircraft, resulting in excellent
speed capabilities, high payload-to-empty-weight ratio, passenger/crew safety and handling and
performance capabilities.
The MD 520N® has been designed to allow a wide variety of rapid configuration options. The
aircraft may be converted rapidly from a personnel transport to a utility cargo configuration. Typical
uses include:
ƒ
Airborne Law Enforcement
ƒ
Search and rescue
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Surveillance and crowd control
ƒ
Aerial survey, patrol and photographic missions
ƒ
Forestry and fire fighting applications
The MDHI MD 520N® helicopter is a turbine powered, rotary-wing aircraft constructed primarily of
aluminum alloy while the NOTAR® system components are primarily graphite composites. The
main rotor is a fully articulated five-bladed system that provides excellent control and
maneuverability characteristics. Power from the turboshaft engine is transmitted through the main
drive shaft to the main rotor transmission. The main transmission drives an intermediate gearbox to
the NOTAR® system fan. An over-running (one-way) clutch placed between the engine and main
rotor transmission, permits freewheeling of the rotor system during autorotation.
The airframe structure is egg-shaped and provides very clean aerodynamic lines. A rigid, threedimensional truss-type structure increases crew safety by means of its roll bar design and reduces
the potential for airframe collapse into the crew and passenger compartments. The airframe
structure is designed to be energy absorbing while maintaining rotor hub integrity.
11.1.1
MD 520N® Outside Dimensions
The fuselage is a semi-monoque structure that is divided into two main sections. The forward
section is composed of the pilot/co-pilot compartment and directly aft, separated by a bulkhead, a
cabin compartment. The pilot compartments equipped with seats for the pilot and either two
passengers on the co-pilot. A canopy of transparent tinted acrylic panels provides excellent
visibility.
An instrument panel is located forward of the seat structure along the aircraft centerline. The panel
incorporates standard flight and engine instruments in addition to warning and caution lights. The
panel also contains adequate space for avionics and flight instruments. An optional “slant panel” is
available that increases the panel space available when extensive avionics suites are selected or
when armament systems are installed.
51
SYSTEM DESCRIPTION
52
SYSTEM DESCRIPTION
Five-Blade Fully Articulated Main Rotor
Crashworthy A-Frame Truss
with Integral Crew Seats
Static Mast Rotor Support
Outstanding Outward Visibility
¨
Anti-Torque System
NOTAR
425 shp Drive System
Simple Mechanical Controls
Rolls-Royce 250-C20R 450 shp Turbine Engine
Flat Cargo Floor
Five-Place Seating Capacity
11.1.2
MD 520N® Inboard Profile and Features
The crashworthy designed fuselage structure beneath the pilot/copilot floor contains space for
the aircraft battery and provision for small cargo storage or installation of avionics equipment.
Access to the compartments is through two floor panels.
The cargo compartment is the center of the aircraft contains provisions for the installation of
passenger seats, auxiliary fuel tanks or cargo/baggage. During cargo-carrying operations, the
compartment floor serves as the cargo deck. The cargo floor is designed to accommodate a
range of cargo requirements.
The aft section includes the structure of the tailboom attachment, NOTAR® system fan and the
engine compartment. Access to the engine compartment is provided through clamshell doors
contoured to the shape of the fuselage.
The lower section is divided by the center “keel beam” and provides housing for the two fuel
cells containing a total of 64 U.S. gallons (242 l) of fuel.
53
SYSTEM DESCRIPTION
11.2 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.
A Rolls-Royce 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
non- rotating 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.
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.
54
SYSTEM DESCRIPTION
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.
11.2.1
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
SYSTEM DESCRIPTION
11.2.2 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
11.3 NOTAR® ANTI-TORQUE SYSTEM
Greater Safety:
ƒ
U.S. FAA, NTSB and U.S. Army Studies have shown that 21 percent of all crashes are due
to tailrotor strikes or loss of tail rotor effectiveness. NOTAR® systems eliminate these
problems.
Reduced Noise
ƒ
Designed and tested to be 50 percent quieter than any other helicopter. This results in
detection distances that are far superior to other aircraft.
Reduced Pilot Workload
ƒ
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
ƒ
11.3.1
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
percent less vulnerable to small arms fire than tail rotor systems on comparable helicopters.
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.
57
SYSTEM DESCRIPTION
11.3.2
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.
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.
11.3.3
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.
58
SYSTEM DESCRIPTION
11.3.4
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.
59
SYSTEM DESCRIPTION
11.3.5
INHERENT SAFETY
The NOTAR anti-torque system eliminates accidents and mishaps caused by the exposed tail
rotor striking 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
the problems associated with quartering tail winds. The power and stability of the MD 520N® in
various wind conditions increase operational safety.
6% All Accidents
Avoidable
14% Accidents
Saved with
NOTAR® System
80% Accidents
Other than Tail
Rotor
11.3.6
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 2.8g’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 percent fewer pilot
controls inputs and rapid turning rates.
60
STANDARD EQUIPMENT
12.0
MD 520N® Standard Equipment
*Required Options Included in Base Price as of 2008
Airframe
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Extended Landing Gear
Rapid Door Removal Hinges (cockpit and cabin)
Tinted Canopy Panels
Tinted Door/window panel-left front
Tinted Door/window panel-left rear
Tinted Door/window panel-right front
Tinted Door/window panel-right rear
Rain Gutter Set
Keyed Locks (4)
Fuselage Hard Points
Jacking Fittings
Passenger Steps
Anti-Collision Lights (3)
Landing light, nose mounted
Position lights
Interior
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LH Rotor Brake
Heater Defogger System
Crew Seats with 4-point Harness Restraint
Passenger Seats with 3-point Harness Restraint
Vinyl and Fabric Cushions
Vinyl Interior Trim Panels
Crew and Cabin Compartment Floor Carpet
Map Case
Fire Extinguisher
First-Aid Kit
Cabin 28-volt Utility Outlet
Battery-Heavy Duty Marathon 17-amp hour
Fresh Air Ventilation System
Cockpit Utility Light
Cabin Convenience Light
Instrument Lighting
Cabin Soundproofing
Cargo Tie-Down Fittings
Rotor and Controls
ƒ
Dual LH Command Flight Controls
61
STANDARD EQUIPMENT
Engine and Electrical
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Rolls-Royce 250-C20R Engine, 450 shp (336 kw)
Automatic engine reignition
Engine wash kit, MD500 series
64 Gallon (242 L) Fuel System
85 amp Starter Generator
External Power Receptacle
Facet Oil Filter
Engine anti-ice
Flight and Engine Instruments
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Engine Particle Separator Filter
Dual tachometer, NR and N2
Engine oil pressure indicator
Engine torque meter
N1 tachometer
Fuel quantity indicator
Digital chronometer
Airspeed indicator
Barometric altimeter
DC ammeter
Outside air temperature indicator
Magnetic compass
Digital/analog turbine outlet temp indicator
Engine oil temp indicator
62
STANDARD EQUIPMENT
Annunciator Panel
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Battery Overtemp Warning Light
Engine Chip Detector Warning Light
Engine Out Warning Light
Fan Transmission Chip Detector Warning Light
Fuel Filter Obstruction Warning Light
Fuel Low Warning Light
Generator Out Warning Light
Low Rotor rpm Warning Light
Main Transmission Chip Detector Warning Light
Main Transmission Oil Pressure Warning Light
Main Transmission Oil Temp Warning Light
Miscellaneous
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Ground Handling Wheels
Engine and Airframe Log Books
Engine Maintenance Manual
Battery Logbook
Flight Manual
Handbook of Maintenance Instructions
Illustrated Parts Catalog
Engine Exhaust Cover
Engine Inlet Cover
Pitot Tube Cover
Main Rotor Blade Tie-Downs
Tail Boom and Thruster Cover
One color paint
63
PERFORMANCE SPECIFICATIONS
13.0
MD 520N® Performance Specifications
Characteristics
at Design Gross Weight
Metric
1361 KG
Imperial
3000 lb.
Metric
1361 KG
Imperial
3350 lb
Maximum Cruise Speed
Sea level
1524 m (5,000 ft)
237 km/hr
245 km/hr
128 kt (147 mph)
132 kt (152 mph)
229km/hr
230 km/hr
123 kt (142 mph)
133 kt (143 mph)
Maximum Permitted Speed
VNE at sea level
282 km/hr
152 kt (175 mph)
282 km/hr
152 kt (175 mph)
Maximum Range
Sea level
1524 m (5,000 ft)
378 km
412 km
204 nm (235 mi)
222 nm (256 mi)
365 km
389 km
197 nm (227 mi)
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
ISA +20° C day
9.7 m/sec
8.6 m/sec
1,913 fpm
1,687 fpm
7.9 m/sec
6.5 m/sec
1,546 fpm
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
907 kg
2,000 lb
907 kg
2,000 lb
Maximum Hook Capacity
Hovering Performance
In-ground effect
Standard day
ISA + 20° C day
3901 m
2743 m
12,800 ft
9,000 ft
2835 m
1554 m
9,300 ft
5,100 ft
Out-of-ground effect
Standard day
ISA + 20° C day
2865 m
1707 m
9,400 ft
5,600 ft
1707 m
427
5,600 ft
1,400 ft
Metric
Imperial
15191 kg
1746 kg
3,350 lb
3,850 lb
719 kg
674 kg
1,585 lb
1,486 lb
WEIGHTS
Characteristics
Maximum Gross Weight
Normal Category
External load operations
Empty Weight
(configurations)
Standard
Industrial
Useful Load
Standard
configuration
Normal Category
External load operations
800 kg
1027 kg
1,764 lb
2,264 lb lb
Industrial
configuration
Normal Category
External load operations
845 kg
1072 kg
1,864 lb
2,364 lb lb
183 kg
403 lb
Metric
Imperial
Usable Fuel Capacity
242 L (64 gal)
POWER PLANT
Characteristics
Rolls-Royce Model 250-C20R
gas turbine, Rated power:
Rated Power
336 kw
450 shp
Derated for reliability and
safety to:
Takeoff Power
Max. Cont. Power
317 kw
280 kw
425 shp
375 shp
64
PERFORMANCE SPECIFICATIONS
13.1 Hover-In-Ground-Effect.
65
PERFORMANCE SPECIFICATIONS
13.2 Hover-Out of-Ground-Effect.
66
PERFORMANCE SPECIFICATIONS
13.3 Takeoff Gross Weight Worksheet.
C20B
Mission #1
1,585 lb
Empty Weight
(719 kg)
170 lb
Pilot
(77 kg)
403 lb
Fuel
(183 kg)
1192 lb
Payload
(540 kg)
3,350 lb
Takeoff GW
(1519 kg)
67
Mission #2
PERFORMANCE SPECIFICATIONS
13.4 Payload vs Range (5,000’, ISA)
68
PERFORMANCE SPECIFICATIONS
13.5 Speed for Best Range
69
PERFORMANCE SPECIFICATIONS
13.6 Speed for Best Endurance
70
PERFORMANCE SPECIFICATIONS
13.7 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.
71
PERFORMANCE SPECIFICATIONS
13.8 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
72
PERFORMANCE SPECIFICATIONS
13.9 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
73
PERFORMANCE SPECIFICATIONS
13.10 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
74
DIRECT OPERATING COST ESTIMATES
14.0
MD 520N® Estimated Direct Operating Cost per Hour (Based upon year 2010US $)
C20R+
Engine
Fuel and Lubricants 1:
Fuel @ $3.93* per gallon @ approx 32 gallons per hour.
Lubricants @ 3% of fuel
Total Fuel ..................................................................................
$ 125.76
$ 3.77
$ 129.53
Airframe Maintenance and Spares2:
Maintenance labor costs:
Scheduled (.15 Manhours/Flight Hours) @ $75.00/Hour*
Unscheduled (.26 Manhours/Flight Hours) @ $75.00/Hour*
$ 11.25
$ 19.50
$ 30.75
Spares Cost:
Scheduled (Inspection) Parts: Used during periodic inspection
i.e. filters, seals, o-rings, etc.......................................................
On-Condition/Unscheduled Part ................................................
Reserves: Component Overhaul (TBO) .....................................
Reserves: Limited-Life Parts .....................................................
Total Airframe Cost ...................................................................
$ 5.78
$ 21.12
$ 45.83
$ 40.99
$ 113.72
Engine3:
Scheduled maintenance labor and parts...........................
Reserve for engine overhaul, spares and
accessories .......................................................................
1
$ 3.00
$ 73.20
Total Engine .............................................................
$ 76.20
Total Direct Operating Cost4 .........................................
$350.20
Fuel cost and labor rate* is based on U.S. Average
Average cost while operating under the following conditions:
Gross Weight: 10% less than maximum certified
Speed: Maximum Range Speed, 117 KIAS306.14
Altitude: 1,000 feet on a standard day
2
Overhaul costs are based on participation in factory exchange program
3
Engine fleet maintenance costs provided by Rolls-Royce Engine Company
4
Indirect costs such as insurance, hangar, salary, etc., are excluded
Cost figures shown are extrapolated from a broad database and are intended for example purposes only.
Actual costs will vary, depending on local operating condition, pricing and supplier practices. We encourage
you top compare these figures with other manufacturers, using the same unit costs for fuel, labor, etc.
75
DIRECT OPERATING COST ESTIMATES
14.1 MD 520N® Direct Operating Cost per Hour Worksheet
„ Fuel and Lubricants
Fuel @ $ per gallon @ approx. gallons per hour……………………………………..
$_________
Lubricants @ ______ % of fuel ………………………………………………………...
$_________
Total Fuel and Lubricants Cost………………………………………………………
$_________(A)
„ 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 Maintenance and Spares Cost…………………………………….
$_________(B)
„ 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 OPERATING COST (A+B+C) ………………………………..
$_________(D)
FIXED OPERATING COST
„ Depreciation
Hull insurance ……………………………………………………………………………
$_________
Liability insurance ……………………………………………………………………….
$_________
Pilot salary ……………………………………………………………………………….
$_________
Hangar rental …………………………………………………………..………………..
$_________
Total Annual Fixed Operating Cost …………………………………….…………..
Total Hours ( ______________ ) flown annually (F) ………………………….……..
$_________(E)
$_________(F)
TOTAL FIXED OPERATING COST PER HOUR (E+F) ………………………….…
$_________(G)
Total Direct Operating Cost Per Hour (from above) ………………….…..………
$_________(D)
TOTAL HOURLY FIXED OPERATING COST (D+G)……………………………….
$_________
76
COMPONENT MAINTENANCE SCHEDULE
15.0
Component Maintenance Schedule
Overhaul Systems
Limited Life Parts
Component
Finite Tiime (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
3,260
Mast
10,450
Transmission Coupling
3,200
Belllcrank
2,870
Control Rod
7,740
Fan Drive Shaft
2,620
Fan Blade Assembly
7,500
Fan Hub
7,500
Pitch Plate
7,500
Rotating Cone Assembly
10,000
Tailboom Assembly
10,000
Tube Torque
5,000
Component
Transmission/MR
M/R Swashplate
M/R Hub
Overrunning Clutch
Starter Generator
Blower Bearings
Fan Bearings
Fan Pitch Plate Bearings
77
Finite Tiime (hr
5,000
2,770
2,770
1,800
1,200
1,200
2,400
2,400
OPTIONAL EQUIPMENT
16.0 MD500 SERIES OPTIONAL EQUIPMENT
Airspeed/Time
ƒ
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lb
0.2
0.4
1.0
Davtron 877 Digital Clock
Heated Pitot Tube, MD 500E/530F
Heated Pitot Tube, MD 520N
Altitude
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lb
Blind Encoder Garmin GAE-43
Encoding Altimeter 3-inch
Instantaneous Vertical Speed Indicator
KRA 10-00 Radar Alt W/KI250 Indicator
KRA405B-15 Radar Alt W/KNI416 Indicator
TRA 3000 Radar Alt with TRI 40 Indicator
Altitude/Heading
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lb
Attitude Gyro Indicator 3-inch
Directional Gyro-Panel Mounted
KCS55A-01 Compass System
KI229-00 Radio Magnetic Indicator
Turn and Bank Indicator, 2-inch
Turn and Bank Indicator, 3-inch (mid continent 1394T100-7Z)
Turn and Bank Indicator, 3-inch United Instruments
Avionics
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ƒ
2.0
3.7
2.5
4.4
10.5
2.6
3.1
3.0
10.3
2.0
1.4
1.6
1.6
lb
GNS-430W NAV/COM/GPS
GNS-430AW NAV/COM/GPS
GNS-530W NAV/COM/GPS
GNS-530AW NAV/COM/GPS
GPS-400-GPS
GPS-500-GPS
GNC-420-COM/GPS
GMA-340 Audio Panel – Stereo
GMA-347 Audio Panel – Stereo, with Panel IPOD Unit
GTX-330D Transponder-Modes A,C,S with TIS Capability
and Diversity Isolation (2 antenna)
GTX-330 Transponder-Modes A,C,S w/o TIS Capability and
Diversity
GTX-327 Transponder-Modes A,C
GMX-200 Multi Function Display Unit
GNC-250 XL – COMM/GPS
GDL-69 Satellite WX – w/o display
GDL-69A Satellite WX with XM radio – w/o display
KLN90B
KT76A Modes A,C Transponder
KT76C Modes A,C Transponder
KT-70 Modes A,C,S Transponder
KDR510 Satellite Weather
Pointer 3000 ELT
78
kg
0.1
0.2
0.5
kg
0.9
1.7
1.1
2.0
4.8
1.2
kg
1.4
1.4
4.7
0.9
0.6
0.7
0.7
kg
7.8
7.8
9.8
9.8
3.5
3.5
4.4
4.4
4.3
2.0
4.3
2.0
4.3
2.0
4.2
4.2
5.2
1.9
1.9
2.4
OPTIONAL EQUIPMENT
Comm/Intercom
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
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ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
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ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
lb
A711 Audio Panel
AA97 Audio Panel System
AMS-42F Dual Channel Audio Panel
AMS-44 Dual Channel Audio Panel
CD Player AM/FM Radio Stereo PS ENG PXE7300
Cyclic Remote Frequency Switch
Garmin GNA-340 Audio Panel
Hand Held Comm Radio Provisions to include AA-34
Universal
Headset Bose Series X Noise Canceling Stereo
Headset David Clark H10-56
Headset David Clark Noise Canceling H10-56HXP
KMA24H-71 Audio Panel
KMA24H-71 Dual Audio Control/Intercom
KTR908 COMM
KX165-25 10-watt COM/NAV Transceiver w/ KI-206 NAV
Indicator
KY196A-30 16-watt VHF COM Transceiver
KY-96A-61 10-watt VHF COM Transceiver
NPX-138N – FM Transceiver 138-174 MHZ
PA Siren System, External w/ AA-22 controller and TS100WR speaker—with recessed mount
Provisions Motorola Spectra 800 MHZ Radio
Rear Seat Transmit Capability, includes AA-12S rear seat
audio panel and 2-each rear lapel cords. NOTE: Compatible
with NAT audio panels
SL-30 COM/NAV
TDFM-6148 VHF HI/UHF LO/800 (136-174/403-512/800)
TDFM-7000 Series 4 R/T System
TFM-550 VHF Low/VHF/UHF High 30-50/138-174/403-512
Wulfsberg RT5000 Transceiver
Wulfsberg C5000 Flex Comm Control Head
Controls
ƒ
ƒ
0.5
0.5
0.7
1.0
2.8
5.2
5.5
3.1
2.4
2.5
1.4
21.4
2.5
9.7
1.1
5.1
5.1
3.1
27.2
4.2
2.3
2.3
1.4
12.3
1.9
lb
2.2
23.0
1.6
KA-22 Avionics Cooling Fan
Lead Acid Battery G641S-17 amp hour
28-volt Cabin and Cockpit Receptacles
Engine
ƒ
ƒ
ƒ
ƒ
ƒ
1.1
1.1
1.5
2.3
6.2
1.0
Electrical System
ƒ
ƒ
ƒ
2.2
1.3
1.3
2.6
2.1
0.1
1.5
lb
Mason Grip Installed – on pilot side only
Right Side Pilot in Command
lb
Diamond J TOT Indicator 61000-34 (C20B Engine)
Diamond J TOT Indicator 61000-35 (C20R Engine)
Engine 250-C20R
Engine Exhaust Oil Breather HT-800
P/C Safety Valve Kit – for C20B Engine Only
79
kg
5.0
2.8
2.8
5.7
4.7
0.3
3.3
kg
0.5
kg
1.0
10.4
0.7
kg
OPTIONAL EQUIPMENT
Environmental
ƒ
lb
Air Conditioning R-134 with Forward Evaporator
Exterior Accessories
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
lb
Breeze Eastern Cargo Hook – require factory hard point
Cargo Hook Load Weigh System – model E51
Cargo Hook with Hard Point
Dual Side Mount – FLR/NightSun – mount only
Exterior Crew Handles (4 each)
Four Bladed Tail Rotor
Meeker Engine Bay Quick Release Hinges
Skid Mirror
Tyler Special Operations Platform
Wire Strike Kit
Exterior Lights
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
Gear/Handling
ƒ
ƒ
ƒ
ƒ
20.0
5.0
10.8
2.1
2.0
9.1
2.3
15.4
7.0
7.0
0.9
kg
19.5
8.8
65.0
65.0
29.5
29.5
23.0
23.0
10.4
10.4
6.7
kg
3.0
lb
kg
lb
kg
Carbide Skid Shoes
Infrared Cameras
ƒ
kg
3.2
lb
Airframe Fuel Filter Install – (500E/N – 503) (500F-505)
Fargo 21 Gallon AUX Fuel Tank
kg
40.3
7.0
lb
Provisions for Side Mounted SX-16 NightSun
Pulse System for Existing Landing Light
Provisions for SX-16 NightSun and Thermal Imager Mounted on
Meeker Dual Side Mount
SX-16 NightSun Side Mounted with Gold Reflector
SX-16 Side Mounted w/o Gold Reflector
SX-5 NightSun – Side Mounted
Night Scanner – 400 Candle Power – Belly Mounted
Super Night Scanner – 800 Candle Power – Belly Mounted
Fuel System
ƒ
ƒ
88.8
FLIR 8500 IR Camera System – Basic No Options – Side
Mounted with Avalex 10-inch Monitor (For Domestic Use Only)
FLIR Equipment – 8500
Provisions for FLIR 7000/8000 Series Nose Mounted, includes
turret mount and monitor; and all cables and wiring. NOTE: Does
not include vibration isolation mount
Slass System for use with FLIR 7000/8000 Series and Wescam
FLIR’s Only
80
OPTIONAL EQUIPMENT
Interior/Trim/Lights
ƒ
ƒ
ƒ
ƒ
ƒ
ƒ
lb
Instrument Panel Face Plate Modification
Leather Covered Interior Panels
Leather Covered Seats
Mesh Seats
NVG Compatible Lighting External and Internal
Slant Panel Pedestal
Mapping Systems
ƒ
ƒ
0
6.0
3.0
lb
kg
lb
kg
Aero Computers LE-5000 Mapping Systems
Metamap Inc.
Windows/Canopy
ƒ
ƒ
ƒ
ƒ
ƒ
kg
0
Comfort Windows – 2 each Cabin, 2 each Cockpit; with slides
Comfort Windwos – 2 each Cabin, 2 each Cockpit; with pop out
Paravion Left Front Door Opener
Paravion Right Front Door Opener
4 Place Door Opener Kit - Paravion
81
1.5
1.5
6.0
0.7
0.7
2.8
PRODUCT SUPPORT PLAN
17.0 PRODUCT SUPPORT PLAN
MD Helicopters, Inc. is dedicated to a successful fielding of its new helicopters and to improve the
support it currently offers operators of its commercial helicopters. In 2008, MD Helicopters, Inc.
introduced the MD Power™ program. This comprehensive support plan provides customers the
opportunity to level budget operating cost. An outline of the plan is presented below. Please
contact a Region Sales Manager or MD Helicopters, Inc. Customer Support for additional details.
MD Power™:
ƒ MD Power™ is designed to provide an owner / operator of a new or pre-owned MD
Helicopter with the ability to budget the cost for airframe parts based upon usage, for
the life of the contract.
ƒ Under MD Power™ the hourly fixed rate covers all inclusive parts replacement at no
additional charge.
ƒ MD Power™ removes risk, and provides budget stability and predictability
ƒ MD Power™ protects cash flow and profits from being affected by unexpected repair
expenses
Added Value, ensuring peace of mind:
ƒ MD provides single point of contact by coordinating
- Rolls Royce Engine Programs
ƒ Removes risk, and provides budget stability and predictability
ƒ Smoothes maintenance costs by reducing the high risk / high cost unscheduled
maintenance events
ƒ Protects cash flow and profits from being affected by unexpected repair expenses
Other Benefits:
ƒ Factory maintenance support through MD Authorized Service Center network
ƒ Provides higher market value upon helicopter resale
ƒ Transferable at time of sale to MDHI approved operator
82
PRODUCT SUPPORT PLAN
MD Power™ Inclusions - Systems and Parts Covered:
The following airframe systems, subsystems, components and/or parts and other systems are included
under MD Power™ unless otherwise excluded:
ƒ MD Drive Train:
- Flight controls, Drive systems, Main rotors, NOTAR system, Hydraulics
ƒ Life-limited parts
ƒ Repair and Overhaul Components
ƒ Main and Tail Rotor Blades
ƒ Airframe electrical systems
ƒ Landing gear
ƒ Mandatory MDHI Service Bulletins or FAA Airworthiness directives
ƒ Rolls Royce 250 or C47 engines under the Rolls Royce Customer Care Elite
Program
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 MD Helicopters, Inc. 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.
Initial 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 MD Helicopters,
Inc. These Technical Representatives are backed up by a factory team of MD Product Support
Engineers who can be called upon at any time to support specific technical issues or questions
that may arise.
Regular Maintenance:
Follow-up visits by MDHI 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, maintenance, rotorcraft flight and
parts manuals are available on the MDHI website (www.mdhelicopters.com) free of charge.
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PRODUCT SUPPORT PLAN
Direct Operating Cost:
The operating cost of MD Helicopters, Inc. are planned to be 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:
MD Helicopters, Inc. 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, MDHI will increase activities
in using customer advanced spares requirement notification to eliminate known spare part
requirements. MD Support Center has been established in Europe, where a significant
inventory of spare parts, exchange components and tools are maintained.
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TRAINING
18.0 TRAINING
The MD Helicopters, Inc. 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
customers/students with the detailed
knowledge of MDHI products that will
increase safety, reduce insurance costs and
result in more efficient operation of the
aircraft. Training is customarily conducted at
the MDHI facility in Mesa, but offsite training
at the customer’s facility can also be
arranged. Training in customer aircraft can
also be arranged.
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:
ƒ
ƒ
ƒ
ƒ
Normal Operations (pattern and hover work)
Normal Operations and emergency procedures
Heavy Weight Performance
Emergency Procedures (auto rotations)
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.
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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 air- craft). 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
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