full PDF 206 specs

Transcription

full PDF 206 specs

PRODUCT SPECIFICATIONS
JANUARY 2005
For additional information visit the Bell Helicopter Textron Website
Homepage: www.bellhelicopter.com
Sales Contact Telephone Numbers
Sales Inquiries
U.S. Toll Free: 800-FLY-BELL
International/US: 817-280-2800
Email: [email protected]
Regional Sales Managers
US/Canada 817-280-3601
Asia Pacific 817-280-2197
Europe/Middle East/Africa 817-280-3261
Latin America 817-280-2713
Fax: 817-280-5037
Marketing Home Office
Manufacturing Facility
Bell Helicopter Textron Inc.
Bell Helicopter Textron Canada Inc
Plant 8, Bldg 40
12,800 rue de l’Avenir
POB 482
Mirabel, Quebec
Fort Worth, TX 76101-0482
Canada J7J 1R4
[email protected]
Fax: 450-437-2006
This book was produced by
Visual Communications Center
POB 482
Ft Worth, TX 76101-0482
PUBLISHERS NOTICE
The data presented in this document is general in nature, and has been compiled
from Bell Helicopter Textron, Inc. [BHTI] source materials including but not limited
to; The Approved Rotorcraft Flight Manual, Maintenance Manual, Illustrated Parts
Catalog, and other engineering design specifications.
This document is intended for the use of BHTI Sales Personnel and for
prospective customers as an aid in determining estimated weight and
performance of the helicopter when configured with equipment for specific
missions.
Disclosure, reproduction, or use of any material in this document by persons
other than BHTI employees, and BHTI independent representatives [International
Dealers] is forbidden without written permission from Bell Helicopter Textron.
The Part Numbers of Optional Equipment [KITS] are subject to revision and
change, and also may be different for specific serial number helicopters or special
custom configurations. Please consult the NOTES found in the right margins of
the optional equipment list pages for equipment compatibility. The continuing
product improvement process of BHTI may cause some components, equipment,
and compatibility to be changed or replaced.
The SPECIFICATIONS, WEIGHTS, DIMENSIONS, AND PERFORMANCE DATA
shown in this document are subject to change without notice.
©Copyright, Bell Helicopter Textron, Inc., 2005
Product
Specifications
®™, Bell Helicopter, Bell Helicopter Textron Inc., Bell
206B3, 206L-4, 407, 427, 430, 412, 609, JetRanger and
LongRanger are registered trademarks of Bell
Helicopter Textron Inc.
1
206B-3
January 2005
EXTERIOR DIMENSIONS
STANDARD LOW SKID GEAR
1.1 FT
(0.33 m)
206B3
STD GEAR
6.4 FT
(1.96 m)
16.7 FT
(5.08 m)
FLAP 8°30' UP
2°15' PRECONE
5° MAST TILT
STATIC DROOP
(BOTH SIDES)
FLAP 8°30' DN
4.2 FT
(1.28 m)
6.8 FT
(2.07 m)
Ø 5.2 FT
(1.58 m)
8.3 FT
(2.52 m)
6.0 FT
(1.82 m)
6.3 FT
(1.92 m)
0.4 FT
(0.13 m)
1.0 FT
(0.30 m)
12.3 FT
(3.75 m)
STATIC GROUND LINE
AT MAX GW 3200 LB (1451 KG) MID CG
8.1 FT
(2.47 m)
1.2 FT
(0.38 m)
32.4 FT
(9.89 m)
19.1 FT
(5.82 m)
39.2 FT
(11.96 m)
OPTIONAL HIGH SKID GEAR w/AAI FLIGHTSTEP ®
1.1 FT
(0.33 m)
206B3
HIGH SKID GEAR
16.7 FT
(5.08 m)
6.4 FT
(1.96 m)
FLAP 8°30' UP
0.4 FT
(0.13 m)
5° MAST TILT
2°15' PRECONE
STATIC DROOP
(BOTH SIDES)
Ø 5.2 FT
(1.56 m)
FLAP 8°30' DN
10.8 FT
(3.28 m)
1.4 FT
(0.41 m)
6.7 FT
(2.04 m)
3.6 FT
(1.10 m)
7.3 FT
(2.22 m)
Product
Specifications
1.9 FT
(0.58 m)
5.7 FT
(1.75 m)
3.8 FT
(1.16 m)
12.3 FT
(3.76 m)
STATIC GROUND LINE
7.5 FT
(2.29 m)
32.5 FT
(9.89 m)
19.6 FT
(5.98 m)
39.7 FT
(12.11 m)
2
206B-3
January 2005
OPTIONAL EMERGENCY FLOAT GEAR w/ AAI FLOATSTEP ®
1.1 FT
(0.33 m)
206B3
FLOAT KIT
16.7 FT
(5.08 m)
6.4 FT
(1.96 m)
FLAP 8°30' UP
0.4 FT
(0.13 m)
5° MAST TILT
2°15' PRECONE
STATIC DROOP
(BOTH SIDES)
Ø 5.2 FT
(1.56 m)
FLAP 8°30' DN
10.8 FT
(3.28 m)
1.31 FT
(0.41 m)
1.28 FT
(0.39 m)
6.9 FT
(2.10 m)
1.9 FT
(0.58 m)
5.7 FT
(1.75 m)
3.8 FT
(1.16 m)
3.3 FT
(1.01 m)
7.3 FT
(2.22 m)
7.5 FT
(2.29 m)
11.5 FT
(3.50 m)
14.8 FT
(4.51 m)
32.5 FT
(9.89 m)
22.0 FT
(6.73 m)
39.7 FT
(12.11 m)
STATIC GROUND LINE
MINIMUM HANGAR SIZE*
7.0 FT X 40.0 FT
[2.2 M X 12.2 M ]
*ALLOWANCE SHOULD BE MADE FOR HIGH SKID GEAR,
GROUND WHEELS, EMPTY FUEL CONDITION, AND DOOR LIP
WHEN CONSIDERING HANGAR DOOR WIDTH AND HEIGHT
Product
Specifications
3
206B-3
January 2005
INTERNAL DIMENSIONS
Product
Specifications
4
206B-3
January 2005
LEFT BLANK
Product
Specifications
5
206B-3
January 2005
SPECIFICATION SUMMARY[U. S. Units]
[Serial No. 4584 & Subsequent]
WEIGHTS
Standard Configuration Weight (Note 1)
Internal Gross Weight [Normal/Optional] (*Note 2 )
External Load Gross Weight
Useful Load (Gross Wt.-Standard Config. Wt.)[Normal/Optional] (*Note 2 )
Maximum External Load (Cargo Hook Limit)
LBS
1713
3200/3350*
3350
1487/1637*
1500
Note 1: Includes twelve (12.0) pounds of engine oil. Ballast is not included in standard configuration weight
(ballast is a function of installed equipment).
PERFORMANCE SUMMARY: (International Standard Day Except as Noted)
• • • REFER TO DEMONSTRATED TAKEOFF & LANDING AND MAXIMUM OPERATING ALTITUDE NOTES ON THE PERFORMANCE CHARTS • • •
TAKEOFF GROSS WEIGHT
LBS
IGE Hovering Ceiling
ISA
ft
(2 ft skid height)
ISA+20C
ft
OGE Hovering Ceiling
ISA
ft
ISA+20C
ft
Certificated Altitude
ISA
ft
Service Ceiling (MCP)
ISA
ft
(100 ft/min)
Sea Level Max R/C (TOP)
ISA
ft/min
Maximum Allowable IAS
ISA, SL
kn
ISA, 5000ft
kn
MCP True Airspeed
ISA, SL
kn
@ Takeoff GW
ISA, 5000ft
kn
Range @ LRC speed
ISA, SL
nm
(Avg. GW, Full Fuel)
ISA, 5000ft
nm
Endurance @ Loiter 52 kn
ISA, SL
hr
(No Reserve)
2600
19,600
16,800
14,900
11,800
20,000
20,000+
3000
15,200
12,300
10,300
7200
20,000
18,200
1940
130
124
121
128
389
452
4.7
1525
130
124
118
122
382
432
4.6
3200
3350
13,200
11,800*
10,200
8800*
5300 (3350lbs@SL)*
3000 (3280lbs@SL)*
13,500
13,500*
13,500
13,500*
1350
122
108
115
115
374
420
4.5
1230*
78*
78*
77*
83*
360*
403*
4.4*
Note 2: Operation at Internal Gross Weight above 3200 pounds requires the Optional STC
Increased Internal Gross Weight to 3350 pounds Kit (FMS-37).
ENGINE POWER RATINGS:
( STANDARD Rolls-Royce 250-C20J ) Uninstalled Mechanical Rating
Takeoff , SHP
Maximum Continuous, SHP
TRANSMISSION RATINGS:
Takeoff , SHP
Maximum Continuous, SHP
FUEL:
Type
Capacity (Usable)
420
370
317
270
Aviation Turbine
91 Gallons
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATIONS FOR
ANY SPECIFIC FLIGHT MISSION, REFERENCE MUST BE MADE TO THE APPROVED FLIGHT MANUAL.
Product
Specifications
6
206B-3
January 2005
SPECIFICATION SUMMARY[Metric Units]
[Serial No. 4584 & Subsequent]
WEIGHTS
Standard Configuration Weight (Note 1)
Internal Gross Weight [Normal/Optional] (*Note 2 )
External Load Gross Weight
Useful Load (Gross Wt.-Standard Config. Wt.)[Normal/Optional] (*Note 2 )
Maximum External Load (Cargo Hook Limit)
KG
777
1451/1519*
1519
674/742*
680
Note 1: Includes 5.4 kilograms of engine oil. Ballast is not included in standard configuration weight (ballast
is a function of installed equipment).
PERFORMANCE SUMMARY: (International Standard Day Except as Noted)
• • • REFER TO DEMONSTRATED TAKEOFF & LANDING AND MAXIMUM OPERATING ALTITUDE NOTES ON THE PERFORMANCE CHARTS • • •
TAKEOFF GROSS WEIGHT
IGE Hovering Ceiling
ISA
(0.6 M skid height)
ISA+20C
OGE Hovering Ceiling
ISA
ISA+20C
Certificated Altitude
ISA
Service Ceiling (MCP)
ISA
(0.5 M/S)
Sea Level Max R/C (TOP)
ISA
Maximum Allowable IAS
ISA, SL
ISA, 1524M
MCP True Airspeed
ISA, SL
@ Takeoff GW
ISA, 1524M
Range @ LRC Speed
ISA, SL
(Avg. GW, Full Fuel)
ISA, 1524M
Endurance, @ Loiter 96 km/h ISA, SL
(No Reserve)
KG
M
M
M
M
M
M
1179
5974
5121
4542
3597
6096
6096+
1361
4633
3749
3139
2195
6096
5547
1451
4023
3109
1615
914
4115
4115
M/S
km/h
km/h
km/h
km/h
km
km
hr
9.9
241
230
224
237
721
837
4.7
7.7
241
230
219
226
708
800
4.6
6.9
226
200
213
213
693
778
4.5
1519
3597*
2682*
(1519Kg@SL)*
(1488Kg@SL)*
4115*
4115*
6.2*
144*
144*
143*
154*
667*
746*
4.4*
Note 2: Operation at Internal Gross Weight above 1451 Kilograms requires the Optional STC
Increased Internal Gross Weight to 1519.5 Kilograms Kit (FMS-37).
ENGINE POWER RATINGS:
( STANDARD Rolls-Royce 250-C20J ) Uninstalled Mechanical Rating
Takeoff , kW
Maximum Continuous, kW
TRANSMISSION RATINGS:
Takeoff , kW
Maximum Continuous, kW
FUEL:
Type
Capacity (Usable)
313
276
236
201
Aviation Turbine
344 Liters
Product
Specifications
7
206B-3
January 2005
JETRANGER III SEATING
CREW SEATING - Two individual ergonomically designed seats with adjustable lumbar support, each equipped
with seat belt, double strap shoulder harness and inertia reel, are located in the cockpit. The color and upholstery material for the seats, and interior trim of the cockpit match that which is selected for the cabin.
STANDARD INTERIOR
STANDARD SEATING & INTERIOR TRIM - The standard cabin seating consists of three equal width seats
with individual seat belts and single strap shoulder harness, arranged across the rear of the cabin. Available
with Red, Blue, Tan, or Gray fabric upholstery with Black seat belts. All vinyl upholstery, or vinyl with fabric
inserts are available as an extra cost option. The standard interior trim consists of plastic closeouts on sidewalls/
window reveals, hat box, fuel cell and control column. The floor is covered in low loop lightweight blend carpet.
The standard seating and interior trim are included in the basic aircraft weight.
Specifications subject to change without notice.
Product
Specifications
8
206B-3
January 2005
CORPORATE INTERIOR
CORPORATE SEATING & INTERIOR TRIM - The corporate cabin seating consists of three equal width seats
with individual seat belts and single strap shoulder harness, arranged across the rear of the cabin. Available
with Pewter, Mushroom, Dark Blue, Saddle, Burgundy, Smoke Grey, and Forest Green upholstery with Black
seat belts. Seats can be all fabric (basic corporate seats), or optional leather with fabric inserts, or all leather with
perforated leather inserts. Carpet is 100% wool cut pile.
Product
Specifications
9
206B-3
January 2005
STANDARD CONFIGURATION
(Items Included In List Price)
AIRFRAME
Oil system, 1.5 gal [5.7 liter] capacity
Compressor wash provisions
Cabin; bonded aluminum honeycomb, and
semi-monocoque structure
Engine mount struts with noise dampers
Doors, four, hinged forward, dual point
latching
Landing gear, tubular skid type with
replaceable skid shoes
Locks for cabin doors and luggage
compartment
Luggage compartment (16 ft3 [.45 M3], 250
lbs [113 Kg]cap), with Composite Door
Provisions for mooring, jacking and single
point lifting
Tail boom, monocoque structure with
vertical fin and fixed elevator
Tail skid (tail rotor guard)
Windshield (and Chin Windows), clear
plexiglass
Windows, blue tinted plexiglass with
sliding panels in doors, Passenger
Cabin "Wedge" Windows
Three color exterior paint scheme
Rain gutters
INTERIOR
Standard 5-place interior with
soundproofing, carpeting, & data case.
Color options available for upholstery &
carpet
5-place shoulder harnesses, dual straps in
cockpit, single strap in cabin
Fire extinguisher, cabin
First aid kit
Parcel shelf (behind aft seat)
Ram air ventilation system
POWERPLANT
Rolls-Royce Model 250-C20J gas
turboshaft engine
Wet spline starter-generator
Fuel boost pumps (2 canister type)
submerged in fuel tanks
Fuel control, Bendix
Fuel filter (eliminates PRIST requirements)
Fuel system, 91 gal. (344 liter) capacity
ROTORS & CONTROLS
Main rotor, semi-rigid, two-bladed, see-saw
type with precone and underslung
feathering axis. All metal blades that are
moisture proofed and epoxy
encapsulated.
Flap restraints.
CHOICE of STANDARD [black top-white
bottom] or HIGH VISIBILITY [orange/white
top-white bottom] painted rotor blades
Tail rotor; semi-rigid, two-bladed, see-saw
type
Hydraulic boost system (pump and reservoir
module)
Mechanical flight control linkages
throughout
TRANSMISSION DRIVE SYSTEM
Focused pylon mounting
Freewheeling unit (between engine and
main transmission)
Gearbox, tail rotor with 2.3:1 spiral bevel
gear reduction
Hydraulic pump (for boost controls)
Main transmission 2 stage 15.22:1 planetary
reduction
Oil cooler
Oil filter with replaceable type cartridge
Oil pump, constant pressure
FLIGHT & ENGINE INSTRUMENTS
Clock, digital quartz chronometer
Compass, magnetic
Dual tachometer (rotor and engine)
Inclinometer
Indicator, airspeed
Indicator, altimeter
Indicator, engine oil pressure/temperature
Indicator, free air temperature
Indicator, fuel quantity
Indicator, fuel pressure/generator load
Indicator, gas producer speed
Indicator, torquemeter pressure
Product
Specifications
10
206B-3
January 2005
STANDARD CONFIGURATION (continued)
(Items Included In List Price)
FLIGHT & ENGINE INSTRUMENTS (cont.)
MISCELLANEOUS
Indicator, transmission oil pressure/
temperature
Indicator, turbine outlet temperature
with over temp light
Hour meter
Covers, turbine inlet and exhaust pipes
Cover pitot tube
Flight bag
Grounding handling wheels w/lift tube
Operating manuals;
Aircraft log book
Engine log book
Engine operating manual
Engine parts manual
Flight manual
Illustrated parts catalog
Maintenance & overhaul manual
Tie-down assemblies, main rotor and
tail rotor
MONITORING SYSTEM
Caution indication lights
Baggage door open
Engine fuel pump inoperative
Engine failure warning
Fuel filter by-pass indicator
Generator failure
Transmission oil pressure
Transmission oil temperature
Chip detectors, magnetic--engine,
main transmission, tail rotor gearbox
Engine out and low rotor RPM warning
lights and horn with mute switch
Battery temperature sensor
Battery hot
Freewheeling unit/magnetic plug
Fuel Low Warning
ELECTRICAL
28 volt DC system
Battery, 17 amp-hr nickel-cadmium
External power and grounding
receptacles
Lights:
Anti-collision strobe
Cockpit/map
Instrument
Landing (two 250 watt)
Position
Starter-generator (150 ampere)
Voltage regulator, Solid State
28 volt outlet in cabin
Heated pitot tube
Product
Specifications
11
206B-3
January 2005
OPTIONAL ACCESSORIES
• • • • • REFER TO NOTES FOR KIT COMPATIBILITY • • • • •
Part Number
Kit Description
Wt (lbs)
Wt (Kg)
Notes
AIRFRAME
206-706-031-109
HIGH SKID GEAR (INCL. AAI FLIGHT STEPS)
206-706-127-111
DUAL CONTROLS
206-706-211-109
LIGHT WEIGHT POP-OUT FLOATS
206-706-510-101
SKID GEAR FAIRINGS
32.2
9.6
14.6 (1, 13
4.4
148.0
67.1 (1
10.3
4.7 (2
AVIONICS
206-705-008-103
VHF EQUIPMENT (KX-155)
7.7
3.5
206-705-008-115
TRANSPONDER PROVISIONS (KT-76A)
1.0
0.5 (3
206-705-008-117
TRANSPONDER EQUIPMENT (KT-76A)
2.5
1.1 (3
206-705-008-131
ADF EQUIPMENT (KR-87)
7.1
3.2
206-705-008-151
OMNI W/ PROVISIONS (KI208)
3.4
1.5
206-705-008-155
TRANSPONDER PROVISIONS (DIGITAL) (KT-70)
1.0
0.5 (3
206-705-008-157
TRANSPONDER EQUIPMENT (DIGITAL) (KT-70)
3.9
1.8 (3
206-705-008-167
VHF/ADF PROVISIONS W/ AUDIO PANEL (KMA24H-71)
206-706-007-101
ENCODING ALTIMETER
10.6
0.9
0.4 (1, 3
4.8
206-706-051-101
BLIND ENCODING ALTIMETER
2.0
0.9 (3
206-706-323-111
FLIGHT INSTRUMENTS [for less Dir. Gyro. See Note/Credits]
10.5
4.8 (4
ENGINE
206-706-038-105
AUTO RE-LIGHT FOR C-20J ENGINE
0.4
0.2
206-706-038-107
AUTO RE-LIGHT ( STC SH4781NM ) FOR C-20R ENGINE
2.4
1.1
206-706-200-111
PARTICLE SEPARATOR
7.3
3.3 (1
STANDARD HEADLINER w/ A/C DUCTS [for STC A/C]
11.0
5.0 (5
206-706-034-107
ROTOR BRAKE
11.6
5.3
206-706-126-105
RESCUE HOIST
35.1
15.9
206-706-126-109
RESCUE HOIST PROVISIONS
11.8
5.4
206-706-136-101
SNOW BAFFLE
0.8
0.4 (12
206-706-214-103
HOIST CABLE GUARD
2.1
1.0
ENVIRONMENT
206-705-400-101
EQUIPMENT
206-706-314-103
LITTER PROVISIONS [Dual Litter System]
16.9
7.7
206-706-324-103
LITTER EQUIPMENT [Two folding litters]
33.0
15.0
206-706-330-101
AUXILIARY 13 AMP HOUR BATTERY (AFT)
206-706-335-101
CARGO HOOK EQUIPMENT
22.7
10.3
206-706-335-107
CARGO HOOK PROVISIONS
4.1
1.9
206-705-717-103
CORPORATE SEATS
0.0
0.0 (1, 11
206-706-039-105
SOUND PROOFING
6.0
2.7 (6
INTERIOR
20.6
9.3
Product
Specifications
12
206B-3
January 2005
OPTIONAL ACCESSORIES (continued)
• • • • • REFER TO NOTES FOR KIT COMPATIBILITY • • • • •
Part Number
Kit Description
Wt (lbs)
Wt (Kg)
Notes
PAINT
HIGH VISIBILITY
MARKINGS FOR HIGH VIS. M/R BLADES (WHITE & ORANGE)
0.0
0.0 (7
113.0
51.3 (5
69.6
31.6 (8
STC's
ENVIRONMENT
206-0102-1
AIR CONDITIONER EQUIPMENT [Air Com]
EQUIPMENT
SX-16C/016551
NIGHTSUN SEARCHLIGHT
965-36502-002
WIRE STRIKE - RECOMMENDED KIT - SEE NOTE
(9
LOW SKIDS
16.4
7.4
HIGH SKIDS
17.4
7.9
PRODUCTION OPTION [NOT A KIT]
680-1000-5
C20/R4 ENGINE OPTION
26.0
11.8 (10
DIRECTIONAL GYRO
-3.6
-1.6 (4
27.0
12.2
-14.8
-6.7
0.0
0.0
Credits
AVIONICS
206-075-606-107
EQUIPMENT
206-050-127-009/010 GROUND HANDLING WHEELS
PAINT
NO EXTERIOR
NO EXTERIOR PAINT
WHITE
WHITE PAINT ONLY
All equipment kits require Provision Kits prior to installation
Notes: For commonality, notes shown below are identical in Product Specification and Price List.
1) Price and/or weight includes credit for basic ship hardware.
2) Only compatible with low skid gear.
3) Encoding Altimeter or Blind Encoder required to enable Mode C or Mode S Altitude reporting.
Customer is responsible for obtaining Aircraft ID code for Mode S.
4)Flight Instruments Less D. G. requires a Sales Order Amendment (Kit number is the SAME).
5) The Standard Headliner with A/C Ducts is required for installation of the STC Air Com airconditioner.
6) Provisions Only - The 13 amp hour battery weighs an additional 24.5 lbs (11.1 kg).
7) Standard or High Visibility Main Rotor Blade Paint to be specified by Sales Order.
8) Requires High Skids.
9)The Wire Strike Kit is a RECOMMENDED extra cost option. The customer must specify on the
Purchase Agreement for the WSPS Kit NOT to be installed.
10) Includes STC Kit 174104-01 (Facet External Engine Oil Filter) 4.0 lbs (1.8 kg.).
11) Material type to be called out on Sales Order. Can be Leather, Fabric/Leather, or Fabric.
12) Particle Seperator and Auto Relight Kits are required for installation of Snow Baffles.
13) "J Steps" (4 each) may be substituted for the AAI FlightSteps by Sales Order. Substitution of "J
Steps" reduce High Skid Kit installed weight by 10.5 lbs (4.8 kg.).
STC Kits - Select Supplemental Type Certificated Optional Equipment Kits are available for installation
at the Bell Helicopter Textron factory. Please contact your Bell Sales Representative for availability and
pricing information.
P.O.R. - Priced On Request.
Product
Specifications
13
206B-3
January 2005
INTENTIONALLY LEFT BLANK
Product
Specifications
14
206B-3
January 2005
HELICOPTER PERFORMANCE
IGE & OGE HOVER, SERVICE CEILING
FOR
STANDARD ROLLS-ROYCE 250-C20J ENGINE
&
OPTIONAL ROLLS-ROYCE 250-C20R/4
ENGINE
BASIC INLET INSTALLED
MINIMUM SPEC. ENGINE
Product
Specifications
15
206B-3
January 2005
STANDARD, ROLLS-ROYCE 250-C20 B/J ENGINE, BASIC INLET
HOVERING CEILING IGE
GROSS WEIGHT - 100 KG
10
11
12
13
14
20
IS
IS
IS
A
A+
10
18
-3
17
16
20
0°
C
C
-1
0°
C
0°
-2
0
56
C
-5
0°
C
°C
-4
0°
C
MU
M
T
13
48
10
30
°C
40
0°
C
°C
IS
A+
10
°C
IS
A+
20
°C
IS
A+
30
°C
20
°C
10
9
30
°C
M
AX
IM
8
44
°C
-10°C
12
11
-2
0
ISA
OA
36
32
28
24
UM
7
OA
T
5
4
3
SKID HEIGHT 2 FT (0.6 M)
2
1
20
16
MAX EXT & OPTIONAL
MAX INT GW 3350 LBS
6
BASIC MAX INT GW 3200 LBS
PRESSURE ALTITUDE - 1000 FT
XI
14
52
-3
0°
C
MA
15
10
°
°C
60
°C
-4
0°
C
°C
°C
°C
30
20
A+
A+
IS
19
-5
0
15
0
PRESSURE ALTITUDE - 100 METERS
9
12
8
4
0
18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34
GROSS WEIGHT - 100 LB
NOTE: TAKEOFF AND LANDING HAS NOT BEEN DEMONSTRATED AND IS NOT APPROVED
ABOVE 16,000 FEET / 4877 METERS DENSITY ALTITUDE.
Product
Specifications
16
206B-3
January 2005
STANDARD, ROLLS-ROYCE 250-C20 B/J ENGINE, BASIC INLET
HOVERING CEILING OGE
13
14
A
10
°C
0 °C
0 °C
18
17
-1
16
0°
-3
0°
-2
0°
C
C
C
-4
0°
C
-5
0
°C
15
14
60
56
52
48
44
40
13
12
11
20
°
MA
C
10
°C
36
0°
C
32
XI
MU
10
M
OA
9
28
T
15
8
24
7
30
6
40
°C
20
°C
16
5
4
12
MAX EXT & OPTIONAL
MAX INT GW 3350 LBS
11
IS
A+
+2
+3
19
IS
IS A
IS A
20
10
9
12
3
8
2
50
°C
4
1
0
0
18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34
Product
Specifications
17
206B-3
January 2005
OPTIONAL, ROLLS-ROYCE 250-C20 R/4 ENGINE, BASIC INLET
HOVERING CEILING IGE
10
11
12
13
20
A
A+
A+
10
°C
°C
°C
30
20
A+
-3
0°
IS
IS
IS
IS
19
-2
0
14
15
60
C
°C
56
18
-1
0°
17
16
10
MA
52
C
-40°C
0°
C
°C
MU
15
M
OA
14
T
48
-20°C
44
-10°C
0°C
40
10°C
36
ISA
13
30
12
ISA+10°C
°C
11
ISA+20°C
20
°C
32
IS
10
A+
30
°C
9
30
°C
M
AX
28
IM
8
24
UM
OA
T
7
20
5
4
3
SKID HEIGHT 2 FT (0.6 M)
2
1
16
MAX EXT & OPTIONAL
MAX INT GW 3350 LBS
6
-30°C
XI
20
°C
-50°C
0
9
12
8
4
0
18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34
Product
Specifications
18
206B-3
January 2005
OPTIONAL, ROLLS-ROYCE 250-C20 R/4 ENGINE, BASIC INLET
HOVERING CEILING OGE
°C
°C
C
17
0°
-1
0°
C
C
°C
10
20
0°
-3
0
14
-5 0
A
A+
A+
+3
-4
0°
C
18
16
13
IS
IS
IS A
19
IS
20
12
°C
-2
0°
C
15
14
60
56
52
48
44
40
13
12
MU
30
°C
M
36
°C
°C
32
OA
10
20
XI
11
10
MA
T
15
9
28
8
24
7
20
6
40
°C
5
16
4
11
MAX EXT & OPTIONAL
MAX INT GW 3350 LBS
10
9
12
3
8
2
4
1
0
0
18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34
Product
Specifications
19
206B-3
January 2005
SERVICE CEILING
STANDARD, ROLLS-ROYCE 250-C20 B/J ENGINE, BASIC INLET AT MCP
100 FPM (0.5 M/S) RATE OF CLIMB
9
10
11
12
13
20
IS
IS
A+
°C
-1
0°
C
18
-3
0°
C
60
-2
0°
C
56
-50°C
17
10
°C
MA
52
0°
C
-40°C
MU
M
20
°C
48
-20°C
44
-10°C
40
10°C
36
OA
-30°C
T
15
14
ISA
13
0°C
ISA+10°C
12
11
ISA+20°C
20°C
ISA+30°C
10
32
30
°C
28
MA
9
X
OA
T
8
7
24
20
5
4
3
2
1
16
MAX EXT & OPTIONAL
MAX INT GW 3350 LBS
6
0
XI
16
A
15
10
°C
°C
30
20
A+
A+
IS
19
IS
14
12
8
4
0
18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34
NOTE: MAXIMUM OPERATING ALTITUDE FOR ALL GROSS WEIGHTS ABOVE 3000
POUNDS/1361 KILOGRAMS IS 13,500 FEET / 4115 METERS DENSITY ALTITUDE.
Product
Specifications
20
206B-3
January 2005
SERVICE CEILING
OPTIONAL, ROLLS-ROYCE 250-C20 R ENGINE, BASIC INLET AT MCP
100 FPM (0.5 M/S) RATE OF CLIMB
10
11
12
13
10
18
-1
°C
°C
°C
30
20
A+
A+
A+
IS
IS
19
0°
C
MA
0°
XI
MU
17
10
°
M
OA
T
16
15
IS
A
IS
20
14
60
-2
0°
C
56
-50°C
C
52
-40°C
C
20
°C
-30°C
48
-20°C
44
-10°C
40
10°C
36
14
ISA
13
0°C
ISA+10°C
12
11
ISA+20°C
20°C
ISA+30°C
10
32
30°C
MAX OAT
9
28
8
24
7
20
5
4
3
2
1
16
MAX EXT & OPTIONAL
MAX INT GW 3350 LBS
6
15
0
9
12
8
4
0
18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34
NOTE: MAXIMUM OPERATING ALTITUDE FOR ALL GROSS WEIGHTS ABOVE 3000
POUNDS/1361 KILOGRAMS IS 13,500 FEET / 4115 METERS DENSITY ALTITUDE.
Product
Specifications
21
206B-3
January 2005
INTENTIONALLY LEFT BLANK
Product
Specifications
22
206B-3
January 2005
FUEL FLOW vs AIRSPEED
ISA & ISA+20°°C
ROLLS-ROYCE 250-C20B/J ENGINE
BASIC INLET INSTALLED
LOW SKID GEAR WITHOUT FAIRINGS
with PLUS ENGINE DATA*
FOR PARTICLE SEPARATOR INSTALLED;
INCREASE FUEL FLOW TWO(2)LB/HR[ONE(1)KG/HR]
FOR CROSS TUBE FAIRINGS;
INCREASE AIRSPEED TWO(2)KNOTS[FOUR(4)KM/HR]
NOTES:
THE BEST ALLOWABLE CRUISE SPEED IS EITHER LONG RANGE CRUISE SPEED
[LRC], OR WHEN SPEED IS LIMITED BY MAXIMUM CONTINUOUS CRUISE POWER
[MCP] OR VNE, THE MAXIMUM SPEED PERMITTED .
* PLUS ENGINE DATA IS SHOWN WHERE THERE IS A SIGNIFICANT DIFFERENCE
BETWEEN MINIMUM SPECIFICATION ENGINE POWER (A "ZERO" ENGINE) AND EITHER
MAXIMUM CONTINUOUS POWER OR THE ENGINE MECHANICAL POWER LIMIT. THIS
DATA IS PROVIDED TO ASSIST PLANNING OF OPERATIONS WHERE FAST CRUISE
SPEED IS DESIRED, BUT THE CONTINUOUS OPERATION LIMITS OF 85% TORQUE AND
/ OR 738 °C ENGINE TOT ARE OBSERVED. THE MAXIMUM ATTAINABLE FAST CRUISE
SPEED WILL BE DETERMINED BY SPECIFIC ENGINE HEALTH (POWER ASSURANCE),
AND OPERATIONAL LIMIT (TORQUE, TOT, N1, OR VNE , WHICHEVER OCCURS FIRST).
PLUS ENGINE PERCENT CAN BE DETERMINED DURING THE ENGINE POWER
ASSURANCE CHECK BY SETTING THE TOT AND RECORDING TORQUE. THE
DIFFERENCE BETWEEN THE RECORDED TORQUE AND THE MINIMUM CHART VALUE
IS THE PLUS PERCENT FACTOR.
Product
Specifications
23
206B-3
January 2005
FUEL FLOW
PRESSURE ALTITUDE = SEA LEVEL
OAT = +15°C
120
TRUE AIRSPEED - KM/HR
160
180
200
220
140
240
210
95
90
95
200
LRC
90
MCP TORQUE LIMIT
85
190
85
80
75
180
65
60
55
50
170
75
VNE
160
70
150
3350
3200
0
300
0
2 80
2600
0
240
140
45
130
40
35
S
OS
R
G
120
VNE
FUEL FLOW - KG/HR
TORQUE - %
70
FUEL FLOW - LB/HR
80
65
S
LB
HT
G
I
WE
60
55
30
50
110
60
70
70
80
90
100
110
120
TRUE AIRSPEED - KNOTS
80
90
100
110
120
INDICATED AIRSPEED - KNOTS
130
130
140
140
Product
Specifications
24
206B-3
January 2005
FUEL FLOW
PRESSURE ALTITUDE = 2000 FEET
OAT = +11°C
120
140
160
180
200
220
240
210
95
95
200
90
90
LRC
85
80
65
60
80
170
75
160
VNE
150
55
50
45
70
VNE
3350
3200
3000
2800
2600
2400
140
130
40
65
60
120
35
FUEL FLOW - KG/HR
70
180
FUEL FLOW - LB/HR
TORQUE - %
75
MCP TORQUE LIMIT
190
85
G
SS
RO
W
TH
EIG
S
LB
55
50
110
60
60
70
70
80
90
100
110
120
80
90
100
110
120
130
140
130
Product
Specifications
25
206B-3
January 2005
FUEL FLOW
OAT = +7°C
120
140
160
180
200
220
240
200
90
90
190
LRC
MCP TORQUE LIMIT
85
85
180
80
80
TORQUE - %
70
65
60
55
FUEL FLOW - LB/HR
75
160
150
65
140
130
45
35
VNE
3350
3200
3000
2800
2600
2400
50
40
70
VNE
120
60
OS
GR
110
FUEL FLOW - KG/HR
170
75
S
L
TH
IG
WE
BS
55
50
30
100
60
60
70
80
90
100
110
120
70
80
90
100
110
130
120
140
130
Product
Specifications
26
206B-3
January 2005
FUEL FLOW
OAT = +3°C
120
140
160
180
200
220
240
200
95
90
190
85
180
90
85
LRC
MCP TORQUE LIMIT
80
VNE
80
70
65
60
75
FUEL FLOW - LB/HR
TORQUE - %
75
160
70
VNE
150
65
140
55
50
45
VNE
3350
3200
3000
2800
2600
2400
130
120
40
35
60
55
SW
OS
R
G
110
FUEL FLOW - KG/HR
170
E
TH
G
I
S
LB
50
100
60
70
60
80
90
100
110
120
70
80
90
100
110
130
140
120
Product
Specifications
27
206B-3
January 2005
FUEL FLOW
OAT = -1°C
120
140
160
180
200
220
240
190
85
90
180
MCP TORQUE LIMIT
85
80
LRC
170
80
75
75
60
55
VNE
VNE
150
65
140
0
335
3200
130
50
3000
2800
2600
2400
120
45
40
70
110
35
100
GR
30
60
FUEL FLOW - KG/HR
65
FUEL FLOW - LB/HR
TORQUE - %
70
160
55
VNE
S
LB
T
IGH
E
SW
OS
50
45
90
60
70
60
80
90
100
110
120
70
80
90
100
110
130
140
120
Product
Specifications
28
206B-3
January 2005
FUEL FLOW
PRESSURE ALTITUDE = SEA LEVEL
OAT = +35°C
120
160
180
200
220
140
240
210
95
90
MCP TORQUE LIMIT
200
85
80
90
190
85
75
180
60
55
FUEL FLOW - LB/HR
TORQUE - %
65
170
160
70
3350
3200
0
300
0
280
0
260
2400
150
50
45
40
35
75
VNE
140
130
VNE
65
S
OS
R
G
120
FUEL FLOW - KG/HR
80
70
W
S
LB
HT
G
I
E
60
55
30
50
110
60
60
70
70
80
90
100
110
120
80
90
100
110
120
130
140
130
Product
Specifications
29
206B-3
January 2005
FUEL FLOW
OAT = +31°C
120
95
210
90
200
160
180
200
220
140
240
95
LRC
90
MCP TORQUE LIMIT
85
190
85
80
180
75
60
55
50
170
75
VNE
160
70
VNE
150
3350
3200
300 0
2800
2600
2400
140
45
130
40
35
30
65
S
OS
R
G
120
FUEL FLOW - KG/HR
65
FUEL FLOW - LB/HR
TORQUE - %
70
80
60
S
LB
HT
IG
E
W
55
50
110
60
60
70
80
90
100
110
120
70
80
90
100
110
130
120
140
130
Product
Specifications
30
206B-3
January 2005
FUEL FLOW
OAT = +27°C
120
160
180
200
220
140
240
200
90
90
LRC
MCP TORQUE LIMIT
190
85
85
MIN SPEC ENGINE MCP
80
180
75
60
55
50
45
40
75
160
VNE
70
150
65
3350
3200
3000
2800
2600
2400
140
130
120
35
VNE
O
GR
110
SS
IGH
E
W
FUEL FLOW - KG/HR
65
80
170
FUEL FLOW - LB/HR
TORQUE - %
70
VNE
60
S
LB
T
55
50
30
100
60
70
60
80
90
100
110
120
130
70
80
90
100
110
120
140
Product
Specifications
31
206B-3
January 2005
FUEL FLOW
OAT = +23°C
120
90
190
85
180
140
160
180
200
220
240
85
MCP TORQUE LIMIT
80
MIN SPEC ENGINE + 4%
80
170
MIN SPEC ENGINE MCP
LRC
75
75
65
60
55
50
FUEL FLOW - LB/HR
TORQUE - %
70
45
40
70
VNE
150
65
140
0
33 5
0
320
130
60
3000
2800
120
110
35
100
GR
30
55
VNE
2600
2400
EIG
W
S
OS
HT
FUEL FLOW - KG/HR
160
S
LB
50
45
90
60
70
60
80
90
100
110
120
70
80
90
100
130
110
140
120
Product
Specifications
32
206B-3
January 2005
FUEL FLOW
OAT = +19°C
120
90
190
85
180
140
160
180
200
220
240
85
MCP TORQUE LIMIT
80
MIN SPEC ENGINE + 4%
80
170
MIN SPEC ENGINE MCP
LRC
75
75
65
60
55
50
45
40
FUEL FLOW - LB/HR
TORQUE - %
70
70
VNE
150
65
140
0
335
0
320
130
60
3000
2800
120
110
35
100
GR
30
55
VNE
2600
2400
OS
EIG
W
S
HT
FUEL FLOW - KG/HR
160
S
LB
50
45
90
60
70
60
80
90
100
110
120
70
80
90
100
130
110
140
120
Product
Specifications
33
206B-3
January 2005
COST OF OPERATIONS
INTRODUCTION
Bell Helicopter Textron's cost of operations data for current production helicopters is based on information from Bell operators and service
facilities.
BHT's Product Support organization accumulates cost data from a diverse group of operators - large, small; sub-polar, subtropical; inland,
coastal; corporate, charter. This information is analyzed to generate sample data for each production model which are averages of the field
experience.
BHT intends to continue monitoring actual costs to enable annual updates of the data to maintain its currency.
The following discussion is provided to review the variables involved in the helicopter's direct and indirect cost of operations as well as its cost
of ownership.
The total cost of helicopter ownership and operation involves both direct and indirect costs. The direct costs are those which are incurred
essentially by the flight hour and include:
Fuel, Lubricants
Basic Airframe Maintenance
Powerplant Maintenance
The indirect costs are not directly dependent upon the number of hours flown and include:
Insurance
Facilities (hangar, workshop, etc.)
Crew Compensation
Financial Factors (depreciation, investment tax credit, financing costs, etc.)
Sample direct operating cost data is available for each current production model. Detailed estimates for total costs relating to specific
operations are available through the BHT regional marketing manager or corporate office using input data supplied by customer/prospect.
DIRECT COSTS
Fuel, Lubricants
A typical average value of fuel and lubricant costs is included in the sample data provided for each model.
Fuel consumption depends upon speed, temperature, externally-mounted accessories, sling loads, etc. A band of approximately 10% more
or less than sample value will cover these factors for normal operations.
Fuel pricing varies considerably based on where the fuel is purchased geographically and whether it is purchased retail or in bulk. The sample
cases use average retail purchase price prevalent at the time of the sample data are prepared.
Basic Airframe Maintenance
Airframe maintenance is divided into four categories:
Periodic Inspections
Overhauls
Replacement of Retirement Parts
Unscheduled
Periodic inspections include those inspection tasks, with their part requirements, listed in the Maintenance Manual for each model.
Man hours for periodic inspections can vary from the sample value provided because of differences in personal experience, tool and parts
availability, facilities, environmental effects such as extremes in working temperatures. Man hour costs/hour are also variable among the
Authorized Service Centers as a result of differences in local costs, overhead expenses and volume of work. The sample value is an average
of costs per hour at Authorized Service Centers at the time of publication.
Overhauls include removal, disassembly, inspection, parts replacement, reassembly and reinstallation of certain components/assemblies at
the periods stated in the BHT Maintenance Manual.
Overhaul man hour and parts requirements are subject to considerable variation depending upon the helicopter's operations and
environments. The sample data reflect average values.
Product
Specifications
34
206B-3
January 2005
COST OF OPERATIONS (continued)
Retirement parts are those which are subject to disposal after an operating time stated in the Maintenance Manual. These are normally
components of the rotors/control systems which are subject to oscillatory loads and are designed and tested for use over a finite number of
flight hours rather than on their condition. The replacement at the required intervals requires some labor which is included in the man hour
data in the sample.
Unscheduled maintenance encompasses labor and parts replacement for major maintenance not covered under the formal Maintenance
Manual requirements for inspections and overhauls. It also includes those additional maintenance requirements imposed by the manufacturer
through issue of Service Bulletins.
The sample data for periodic inspections provide for some minor unscheduled maintenance tasks resulting from the inspection.
Powerplant Maintenance
The powerplant (engine [s]) requires periodic inspection and overhauls. The overhaul periods are based on the number of operating hours
or on the number of cycles, whichever is the first limit to be attained. Start cycles are a factor because thermal cycles are important in the design
of the turbine engine's rotating components. Overhauls are performed by the engine manufacturer and/or at authorized facilities.
Powerplant overhaul can be performed for the engine as a unit, or in some cases for individual modules. (Modules can be gearbox, compressor,
turbine, for example.) Each module can have its own overhaul period. Modular overhaul can be cost-effective for some operations and it use
should be evaluated.
Engine or module exchanges can be made in lieu of overhaul. For details, contact the engine manufacturer or his authorized distributors/service
centers. The sample costs are based on an average exchange.
The powerplant may also require unscheduled maintenance (unscheduled removals for repair, parts replacement).
INDIRECT COSTS
Insurance
Insurance rates are based on a number of factors including claim experience, type of operations, and crew qualifications. Rates can be obtained
from insurance agent/broker.
Facilities
Facilities can include hangar, workshop, parts storage area, tools, ground support equipment and administrative area as appropriate to the
specific operation.
Crew Compensation
The number of aircrew personnel depends on the individual operation; i. e., whether the normal crew consists of one or two pilots, hours per
day flown, backup requirements for illness, vacation, etc.
Bell regional marketing managers can advise typical local costs for estimation purposes.
Financial Factors
Funding a helicopter purchase can be accomplished in a variety of ways, including cash, short term note, long term note, partnership, etc. For
investment accounting, several depreciation methods also exist; straight line, double declining, sum of the years digits, etc. Value of resale
is a significant factor.
Miscellaneous Factors
Staff expenses (other than aircrew and direct maintenance personnel), utilities, office expenses, etc.
OWNERSHIP ANALYSIS PROGRAM
Bell Helicopter Textron uses the Life Cycle Cost 2005 computer program provided by Conklin & de Decker Associates, Inc. to determine
ownership costs for an operators planned period of utilization for the aircraft. Conklin's Rotorcraft Analysis Office may be contacted at: Phone;
(817)277-6403 or Fax; (817)277-6402.
Bell's regional marketing managers or corporate office personnel will be able to assist in preparing an ownership analysis which is customized
for our customers specific individual conditions and needs.
Product
Specifications
35
206B-3
January 2005
SAMPLE - COST OF OPERATIONS
U S DOLLARS PER FLIGHT HOUR
Operator
Overhaul
Fuel and Lubricants
Fuel: (Note 1 ) [28 Gal/Hr]
$63.00
Lubricants: 3% of Fuel Cost
1.89
Airframe Direct Maintenance
Labor: (Note 2 )
Inspection
(0.310 MH/FH)
20.13
Overhaul
(0.099 MH/FH)
6.42
Unscheduled and on-condition
(0.379 MH/FH)
24.65
Parts:
Inspections
2.48
Retirement
35.24
Overhaul
17.73
Unscheduled and on-condition
32.30
Powerplant Direct Maintenance
Overhaul (Including Accessories-Note 3)
51.94
Line Maintenance (labor)
(0.067 MH/FH)
TOTAL AVERAGE COST / HR
4.33
$260.11
Note 1: Fuel at $2.25 per gallon. Average fuel consumption for LRC at 1000 feet, ISA,
( Jet-A at 6.8 Lb/Gal.)
Note 2: Labor rate assumed at $65.00 per hour.
Note 3: Includes all scheduled and unscheduled maintenance and life limited parts
replacement assuming normal operating environment.
Product
Specifications
36
206B-3
January 2005
LIMITED LIFE COMPONENTS
LIFE
(FLT HRS)
QTY
PER A/C
MAIN ROTOR HUB AND BLADE
206-010-200-133
Main Rotor Blade
206-011-113-103
Main Rotor Trunnion
206-011-125-105
Main Rotor Strap Pin
206-011-132-113A Main Rotor Grip
206-011-150-105
Retention Strap Fitting
206-011-154-107
Tension-Torsion Strap
206-011-260-103
Retention Strap Bolt
5,000
4,800
2,500
4,800
2,400
1,200
2,500
2
1
2
2
2
2
2
$
$
$
$
$
$
$
31,098
2,220
375
7,397
1,666
3,573
636
$
$
$
$
$
$
$
12.44
0.46
0.30
3.08
1.39
5.96
0.51
MAIN ROTOR CONTROLS
206-001-194-001
Lower Collective Tube
206-001-566-101
Servo Actuator Support
206-010-407-001
Collective Lever Idler Link
206-010-452-113
Swashplate Support
206-010-454-109
Swashplate Sleeve Assy
206-010-467-105
Collective Lever
4,800
10,000
4,800
4,800
4,800
4,800
1
1
1
1
1
1
$
$
$
$
$
$
687
11,416
863
6,175
3,316
1,249
$
$
$
$
$
$
0.14
1.14
0.18
1.29
0.69
0.26
POWERTRAIN
CL42250-1
3,000
1
$
2,138
$
0.71
TAIL ROTOR HUB AND BLADE
206-011-819-109
Tail Rotor Yoke
206-016-201-131
Tail Rotor Blade
206-011-803-005
Tail Rotor Trunnion
5,000
2,500
2400
1
2
1
$
$
$
4,666
5,965
1,180
$
$
$
0.93
4.77
0.49
TAIL ROTOR GEARBOX
206-040-410-101
Duplex Bearing
3,000
1
$
1,480
$
0.49
$
35.24
PART NUMBER
COMPONENT
Freewheeling Unit Clutch
LIST
TOTAL COST
PRICE EA
(FLT HR)
TOTAL
M/R Hub
Mast Assy
Transmission
COMPONENT OVERHAUL INTERVALS (HOURS)
2,400 Freewheeling Assy
3,000
T/R Hub
3,000 Swashplate & Support
4,800
Hyd Pump/Resv & Servos
4,500 T/R Gearbox
6,000
T/R Drive System
2,500
3,600
3,000/3 yrs
Prices and hours are subject to change without notice.
THESE DATA ARE PROVIDED FOR ILLUSTRATION PURPOSES. CONSULT MAINTENANCE DOCUMENTS AND BHT SPARE PARTS PRICING FOR CURRENT, OFFICIAL
INFORMATION.
Product
Specifications
37
206B-3
January 2005
PAINT SELECTION NOTES:
1. COLOR RENDERINGS (ORIGINAL) MUST BE PROVIDED FOR ANY DEVIATION TO
THE STANDARD SCHEMES (ALL MODELS).
2. CUSTOM PAINT SCHEMES TO CUSTOMER SPECIFICATION ARE AVAILABLE, AND
A PRICE QUOTE WILL BE PROVIDED ON REQUEST. PLEASE PROVIDE AS MUCH
DETAIL AS POSSIBLE WHEN DESCRIBING SPECIAL INSTRUCTIONS AND CUSTOM
PAINT SCHEMES.
3. THE DANGER ARROW IS ALWAYS APPLIED ON THE TAIL BOOM BETWEEN THE
HORIZONTAL STABILIZER AND THE TAIL ROTOR, NOT WITHSTANDING ANY OTHER
ILLUSTRATIONS.
4. UNLESS CLEARLY SPECIFIED (LOCATION, DIMENSION, COLOR), REGISTRATION
MARKINGS WILL BE APPLIED PER FAA REGULATIONS (ALL MODELS).
5. METALLIC PAINT CAN NOT BE APPLIED OVER RADOME AREAS WHEN A RADAR IS
INSTALLED.
6. PLACEMENT OF BELL MODEL LOGOS IS EFFECTED BY INDIVIDUAL PAINT SCHEMES,
AND WILL BE APPLIED AT THE DISCRETION OF BELL HELICOPTER UNLESS
OTHERWISE SPECIFIED BY THE CUSTOMER.
Product
Specifications
38
206B-3
January 2005
CUSTOMER
SERIAL NO.
REGISTRATION NO.
Standard Scheme A #206B-5/99-A
BASE COLOR
ACCENT COLOR
MAJOR COLOR
NAME
NAME
NAME
NUMBER
NUMBER
NUMBER
Standard Scheme B #206B-5/99-B
BASE COLOR
ACCENT COLOR
MAJOR COLOR
NAME
NAME
NAME
NUMBER
NUMBER
NUMBER
Standard Scheme C #206B-5/99-C
BASE COLOR
ACCENT COLOR
MAJOR COLOR
NAME
NAME
NAME
NUMBER
NUMBER
NUMBER
ACCENT COLOR
NAME
NUMBER
BASE COLOR
NAME
NUMBER
REGISTRATION NO.
SERIAL NO.
CUSTOMER
Custom Scheme
NUMBER
NAME
MAJOR COLOR
STANDARD PAINT SCHEMES
COLOR SELECTION SAMPLES
A
206B3-5/99-A
B
206B3-5/99-B
C
206B3-5/99-C
P.O. Box 482, Fort Worth, Texas 76101,
Phone: (817) 280-2800, Fax: (817) 278-2800
www.bellhelicopter.textron.com
BELL HELICOPTER TEXTRON
DIVISION OF TEXTRON CANADA LTD.
12,800 rue de l' Avenir Mirabel, Quebec, Canada J7J1R4
Phone: (450) 437-2729 Fax: (450) 437-2066
The data set forth in this brochure are general in nature and may vary with conditions. For performance data and operating
limitations for any specific flight mission reference must be made to the approved flight manual.
Written, Edited and Layout by:
Dave Wyatt
817-280-6918
E-Mail Address: [email protected]
© 2005 Bell Helicopter Textron Inc.
All Rights Reserved.
Printed in USA
January 2005

full PDF 206 specs

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