Bell 429 Product Specifications

Bell 429 Product Specifications

Rev 1 - September 2009

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Bell 429 Product Specification

Table of Contents Publishers Notice..............................................................................................................................................................1 External Dimensions.........................................................................................................................................................3 Specification Summary (U.S. Units) .................................................................................................................................4 Specification Summary (Metric Units) ..............................................................................................................................5 Bell BasiX-Pro® Integrated Avionics System ...................................................................................................................6 Automatic Flight Control System ......................................................................................................................................7 Bell BasiX-Pro® Integrated Avionics SystemWith Optional Kits Installed ........................................................................8 429 Seating ....................................................................................................................................................................10 429 Seating .................................................................................................................................................................... 11 Standard Configuration (Items Included in List Price) ......................................................................................12 Optional Accessory Kits ..................................................................................................................................................14 Fuel Flow Charts - ISA & ISA+20OC ..............................................................................................................................17 Performance Charts - IGE & OGE Hover and Service Ceilings .....................................................................................30

Bell 429 Product Specification

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Bell 429 Product Specification

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 Inc. The listings 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.

©2009 Bell Helicopter Textron Inc.

Bell 206B3, 206L-4, 407, 427, 430, 412, 429, 609, JetRanger and LongRanger are registered trademarks of Bell Helicopter Textron Inc. All rights reserved.

Specifications subject to change without notice. Bell 429 Product Specification

1

Rev. 1 - September 2009

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Rev. 1 - September 2009

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Bell 429 Product Specification

External Dimensions

Specifications subject to change without notice. Bell 429 Product Specification

3

Rev. 1 - September 2009

Specification Summary (U.S. Units) Weights

lbs

Standard Configuration Weight (Note 1)

4425

Normal Gross Weight (Internal Load)

7000

External Gross Weight

7500

Standard Configuration Useful Load (Normal GW – Standard Config. Weight)

2575

Maximum External Load (Cargo Hook Limit)

3000

Performance Summary: Takeoff, Gross Weight IGE Hovering Ceiling

ISA

OGE Hovering Ceiling

lbs

5500

6000

6500

7000

ft

20,000+

18,577

16,301

14,132

ISA+20

ft

17,969

15,487

13,102

10,839

ISA

ft

18,390

15,888

13,535

11,282

ISA+20

ft

15,347

12,744

10,287

7963

Service Celing (MCP) - AEO

ISA

ft

20,000+

20,000+

20,000+

18,714

(30 minute) - OEI

ISA

ft

16,690

14,209

11,871

9629

(continuous) - OEI

ISA

ft

15,670

13,153

10,728

8443

SL, ISA

ktas

154

153

152

150

SL, ISA+20C

ktas

154

153

151

149

4000 ft, ISA

ktas

155+

155+

155+

155

4000 ft, ISA+20C

ktas

153

151

149

145

Maximum Cruise Speed (true airspeed)

Cruise at Long Range Cruise (LRC) Speed Range (standard fuel, no reserve)

SL, ISA

LRC Speed (average true airspeed) Range (standard fuel, no reserve)

246

376

378

368

128

128

129

130

4000 ft, ISA

nmi

271

413

414

407

ktas

128

129

130

129

SL, ISA

hr

2.8

4.2

4.2

4.0

4000 ft, ISA

hr

3.0

4.6

4.5

4.4

LRC Speed (average true airspeed) Endurance at Loiter Speed (60 kts) (standard fuel, no reserve)

nmi ktas

Uninstalled Thermodynamic Power

Engine Rated Power

SHP

719

598

Max Continuous Power

SHP

635

586

OEI (30 seconds)

SHP

826

729

Engine Ratings: (100% RPM) Pratt & Whitney Canada PW207D1 with Full Authority Digital Electronic Control (FADEC) Takeoff (5 minutes)

OEI (2 minutes)

SHP

784

701

OEI (30 minutes)

SHP

753

663

OEI (continuous)

SHP

719

655

Transmission Ratings: (100% RPM) Takeoff (5-minute)

SHP

1100

Max Continuous

SHP

1100

OEI (30 seconds)

SHP

729

OEI (2 minutes)

SHP

650

OEI (30 seconds & continuous)

SHP

550

Fuel Capacity (usable): Standard

216.9 US Gallons

Auxiliary (optional)

39.2 US Gallons

* Refer to demonstrated takeoff and landing and maximum operating altitude notes on the performance charts Note 1: Standard configuration includes all items listed in the Standard Configuration section of this document as well as 24 pounds of engine oil. Ballast is not included in the standard configuration (ballast is a function of installed equipment).

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 Rev. 1 - September 2009

4

Bell 429 Product Specification

Specification Summary (Metric Units) Weights

KG

Standard Configuration Weight (Note 1)

2007

Normal Gross Weight (Internal Load)

3175

External Gross Weight

3402

Standard Configuration Useful Load (Normal GW – Standard Config. Weight)

1168

Maximum External Load (Cargo Hook Limit)

1361

Performance Summary: Takeoff, Gross Weight IGE Hovering Ceiling

ISA

OGE Hovering Ceiling Service Celing (MCP) - AEO

KG

2495

2722

2948

3175

m

6096+

5662

4969

4307

ISA+20

m

5477

4720

3993

3304

ISA

m

5605

4843

4125

3439

ISA+20

m

4678

3884

3135

2427

ISA

m

6096+

6096+

6096+

5704

(30 minute) - OEI

ISA

m

5087

4331

3618

2935

(continuous) - OEI

ISA

m

4776

4009

3270

2573

SL, ISA

km/hr

285

283

281

278

SL, ISA+20C

km/hr

285

283

280

276

Maximum Cruise Speed (true airspeed)

1220 m, ISA

km/hr

287+

287+

287+

287

1220 m, ISA+20C

km/hr

283

280

276

269

SL, ISA

km

456

696

700

682

km/hr

237

237

239

241

km

502

765

767

754

Cruise at Long Range Cruise (LRC) Speed Range (standard fuel, no reserve) LRC Speed (average true airspeed) Range (standard fuel, no reserve)

1220 m, ISA

LRC Speed (average true airspeed)

km/hr

237

239

241

239

SL, ISA

hr

2.8

4.2

4.2

4.0

1220 m, ISA

hr

3.0

4.6

4.5

4.4

Endurance at Loiter Speed (111 km/hr) (standard fuel, no reserve)

Uninstalled Thermodynamic Power

Engine Ratings: (100% RPM) Pratt & Whitney Canada PW207D1 with Full Authority Digital Electronic Control (FADEC) Takeoff (5 minutes)

Engine Rated Power

kW

536

446

Max Continuous Power

kW

473

437

OEI (30 seconds)

kW

616

544

OEI (2 minutes)

kW

585

523

OEI (30 minutes)

kW

561

494

OEI (continuous)

kW

536

488

Transmission Ratings: (100% RPM) Takeoff (5-minute)

kW

820

Max Continuous

kW

820

OEI (30 seconds)

kW

544

OEI (2 minutes)

kW

485

OEI (30 seconds & continuous)

kW

410

Fuel Capacity (usable): Standard

821.1 Liters

Auxiliary (optional)

148.4 Liters

* Refer to demonstrated takeoff and landing and maximum operating altitude notes on the performance charts Note 1: Standard configuration includes all items listed in the Standard Configuration section of this document as well as 11 kilograms of engine oil. Ballast is not included in the standard configuration (ballast is a function of installed equipment).

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 Bell 429 Product Specification

5

Rev. 1 - September 2009

Bell BasiX-Pro® Integrated Avionics System

429-MD-1-0004d

Specifications subject to change without notice. Rev. 1 - September 2009

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Bell 429 Product Specification

Automatic Flight Control System

AMAA-2210-000001

Specifications subject to change without notice. Bell 429 Product Specification

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Rev. 1 - September 2009

Bell BasiX-Pro® Integrated Avionics System With Optional Kits Installed

Specifications subject to change without notice. Rev. 1 - September 2009

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Bell 429 Product Specification

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Bell 429 Product Specification

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Rev. 1 - September 2009

429 Seating CREW SEATING – Two individual ergonomically designed energy attenuating seats with adjustable lumbar support, each equipped with seat adjustment controls, adjustable lumbar support, a four-point restraint system, and adjustable pedals. The color and upholstery material for the seats match the color scheme selected for the cabin. PASSENGER CABIN SEATING OPTIONS – Five passenger seating options are available for selection (ref. Optional Accessory Kits, page. 10), two standard seating options and three corporate seating options. Standard Six Place Seating: Standard seating consists of two rows of three energy-absorbing seats, with individual 4-point restraint system, quick release disconnects and fixed provisions for a passenger cabin ICS system. Each passenger seat assembly is installed on two transverse tracks that are attached to the cabin floor. The quick release disconnects enable the seats to be quickly arranged into either an airline configuration with both rows facing forward, or a club configuration with the two rows facing each other. The seats are upholstered in fabric. Vinyl seat upholstery and reinforced vinyl “Aermat” floor covering are available at extra cost. The passenger seats are available in either a standard 15.5” seat width or a standard wide 18.5” seat width. The standard interior trim consists of full thermoplastic closeouts on all airframe areas and a molded thermoplastic headliner with two fixed slotted air vents. A headliner with LED lights and adjustable air conditioning vents is available as an optional accessory.

Standard Six Place Passenger Seating – Airline Arrangement

Note: Passenger seats, carpeting and aft cabin bulkhead closeout panel are optional accessory kits, not included in Standard Configuration weight and price.

Specifications subject to change without notice. Rev. 1 - September 2009

10

Bell 429 Product Specification

429 Seating Corporate Seating Options: Three corporate seating options are available: • Six place seating with 18.5” wide plush seats • Five place club seating with a row of two 21.5” seats separated by a center console facing a row of three 18.5” seats • Four place club seating with two 21.5” seats separated by a center console on each side All corporate seating options include individual 3-point restraint system, quick release disconnects and fixed provisions for a passenger cabin ICS system. For the five place club seating option, the quick release disconnects enable the seats to be quickly arranged with the two 21.5” seats facing either forward or aft. The seats are upholstered in premium leather, and the floor is covered with plush wool carpet. The corporate interior trim consists of full thermoplastic panels on all airframe areas with color coordinated leather or fabric trim, and a molded thermoplastic headliner with LED lights, adjustable air conditioning vents and color coordinated leather trim.

Corporate Five Place Club Passenger Seating Arrangement

Note: Passenger seats, carpeting and aft cabin bulkhead closeout panel are optional accessory kits, not included in Standard Configuration weight and price.

Specifications subject to change without notice. Bell 429 Product Specification

11

Rev. 1 - September 2009

Standard Configuration (Items Included in List Price)

Certified for Single Pilot IFR and Category A Operations at MGW Certification Basis: FAR Part 27 Amendment 44, 2008 (Most current Certification Standard) AIRFRAME

Two elastomeric forward/aft restraints

Fuselage: Machined alloy airframe with single piece machined roof beams, lift frames, cabin keel beams and nose beams; carbon fiber composite side-bodies, belly panels, nose skins, floor panels, decks and engine cowls

Three main transmission chip detectors Two transmission-mounted hydraulic pumps Tail rotor drive shaft: Two steel forward drive shafts in engine deck/fire zone

Corrosion resistant design with wet installed fasteners and sealed surfaces where dissimilar materials are found to provide exceptional resistance to adverse environmental conditions

Two interchangeable carbon fiber composite aft drive shafts in tailboom zone Single stage 90O tail rotor gearbox

Doors (six, carbon fiber): Hinged pilot & co-pilot doors with sliding windows; hinged forward and sliding aft passenger doors on both sides.

One tail rotor gearbox chip detector ROTORS AND CONTROLS

Passenger doors provide 59 inches unobstructed opening on each side.

Main rotor: Soft-in-plane system, 36 ft. diameter, four interchangeable M/R blades, with stacked composite yokes, titanium drive plate and CF fittings, elastomeric CF bearings and shear restraints, and elastomeric lead/lag dampers

Door Locks for cabin doors and luggage compartment Luggage compartment: Aft cabin (74 cubic feet), with 16 discrete tie-down hardpoints and R/H side external luggage door

Composite M/R blades with Nickel-Cobalt leading edge abrasion strips and tip caps, HIGH VISABILITY (orange/white top - white bottom) paint scheme

Landing gear: Tubular skid type with replaceable wear shoes

Tail rotor: Four blade stacked system, 65” diameter, with low tip speed, scissor arrangement, composite T/R blades with swept blade tips, Nickel-Cobalt leading edge abrasion strips, and elastomeric flapping bearings

Tailboom: Carbon fiber tailboom, vertical fin and horizontal stabilizer Fuselage mounted passenger cabin steps, forward mounted crew steps, and aft maintenance step

Dual Hydraulic System with integrated hydraulic modules

Provisions for mooring, jacking and single point lifting

Mechanical flight controls throughout

Windows: Gray tinted acrylic windows and windshields

Collective mounted throttle controls

Wire Strike Protection System Fixed Provisions

Dual Pilot Control Provisions

Air Conditioning Fixed Provisions

Rotor Brake

Bleed Air Heater Fixed Provisions

FLIGHT & ENGINE INSTRUMENTS – Bell BasiX-Pro Integrated Avionics System

Three color exterior paint schemes, Sample illustrations available upon request

EFIS/EICAS (Electronic Flight Instruments System/ Engine Indicating & Crew Alerting System)

POWERPLANT

Two 6” x 8” colour LCD displays with video display capability

Two Pratt & Whitney Canada 207D1 Engines, 1,172 shp, (Mechanical) Maximum Continuous Rating (586 shp per engine)

“Smart” programmable display unit provisions for future interface required for customized equipment installations

Electronic Engine Controls (EEC)

Aircraft Data Interface Unit, Dual Channel

Fuel Management Module (FMM)

AFCS (3-axis), Dual digital autopilot

Fuel system: 216.9 gal. (820 liter) usable capacity, with three rupture resistant fuel cells located under the cabin floor panel and suction-type fuel feed system

Dual channel SCAS and trim actuators

Inlet Barrier Filter & Electrical Provisions

AD/AHRS (Air Data/Attitude Heading Reference System), Dual Channel (Honeywell KSG7200)

Engine Fire Detector & Dual Bottle Fire Extinguisher System

Course/Heading/Flight Director Panel

TRANSMISSION AND DRIVE SYSTEMS

Standby Instruments: Attitude, Altitude, Heading and Airspeed

Two-stage dual input drive main transmission, 1,100 shp Maximum Continuous Power

Electronic Data Recorder embedded in the IAS (Integrated Avionic System) (non-crashworthy)

Two fluid filled pylon mounts LIVE suspension (left and right vertical axis mounts) Specifications subject to change without notice. Rev. 1 - September 2009

12

Bell 429 Product Specification

Standard Configuration (cont) (Items Included in List Price)

Certified for Single Pilot IFR and Category A Operations at MGW Certification Basis: FAR Part 27 Amendment 44, 2008 (Most current Certification Standard) COMMUNICATIONS & NAVIGATION

ELECTRICAL

Nav/Comm/GPS: VOR/ILS/GS/COMM/GPS and WAAS (Wide Area Augmentation System), with two 1.8”h x 3.3”w” displays (Garmin GNS 430)

28 volt DC system, dual generator configuration 53 AmpH Increased Capacity Battery, Sealed Lead-Acid (required for Cat. A Operations)

Transponder: ELS compliant Mode S (Garmin GTX 330) Dual Keyed and/or VOX Intercom System

Two 200 Amp Starter Generators, with two generator-regulator control units (required for Cat. A. Operations)

Marker Beacon Receiver

External power source connection

Radar Altimeter (Honeywell KRA 405B) (Required for Cat. A Operations

LED Cockpit instrument, annuciator, utility and map lighting with programmable lighting power supply to ensure light balancing across all cockpit display and control panels

ELT (ARTEX C406-N-HM)

All LED basic external lighting system: landing light, anticollision light and position lights

INTERIOR Open cabin design with flat floor, total contiguous cabin volume 232 cu. ft. (passenger and aft cabin area volume 204 cu. ft.)

Digital maintenance interface available from cockpit for all digital aircraft systems RADS wiring for sensors embedded in basic aircraft wiring

Standard cockpit seating (2 seats), adjustable forward & aft, up & down, with lumbar support and adjustable pedals

Baggage compartment lighting Electrical Provisions Kit (Required for Cat. A Operations): Fixed provisions for Rotor Brake, ELT, Radar Altimeter, Articulated Landing Light and Windshield Wipers

Ram air cockpit and cabin ventilation system Standard Interior (Thermoplastic panels covering all doors) Standard Headliner, Passenger Cabin, with two fixed slotted side air vents

High Intensity Discharge Articulated Landing Light (Required for Cat. A Operations)

Note: Passenger Cabin interior, headliner and seating options available for the 429 are listed in the Optional Accessory Kits section.

MISCELLANEOUS Keys for crew, passenger and baggage compartment doors Manuals – Flight, Maintenance and Illustrated Parts Breakdown/Special Tools Catalogue Main and tail rotor tie downs Cargo tie downs (loose equipment) Covers – engine air, oil cooler, exhaust and pitot Ground handling wheels, hydraulic

Specifications subject to change without notice. Bell 429 Product Specification

13

Rev. 1 - September 2009

Optional Accessory Kits Refer to notes for kit compatibility. Additional Kits and STC Items may be available for factory installation. Please consult sales or contract personnel regarding special needs prior to selection of final configuration Part Number

Projected Availability Status

Wt (lbs)

Wt (kg)

Notes

Dual Pilot Controls Equipment (does not include co-pilot head set) (Required for Dual Pilot IFR)

429-706-701-101



6.6

3.0

1

Pilot Cyclic Stick Locking Device

429-706-704-101

0.2

0.1

Aux. Fuel Tank Equipment (40 US Gal.)

429-706-500-101

 

60.2

27.3

Windshield Wiper (Pilot)

429-706-030-101

3rd Quarter 2009

9.4

4.3

Windshield Wiper (Co-pilot)

429-706-030-103

3rd Quarter 2009

6.6

3.0

Rear Clamshell Doors with windows

429-706-002-101 Effectivity: s/n 57001 - 57016



28.0

12.7

Rear Clamshell Doors with windows

429-706-002-103 Effectivity: s/n 57017 & subsequent



28.0

12.7

Emergency Floats without life rafts (Aerazur) (life vests not included)

221035-0

1st Quarter 2010

145.5

66.0

Emergency Floats with one life raft, Left side (Aerazur) (life vests not included)

221036-0

1st Quarter 2010

197.3

89.5

Emergency Floats with two life rafts, Left & Right side (Aerazur) (life vests not included)

221030-0

1st Quarter 2010

249.0

112.9

Ditching Kit (additional strengthening to a/c nose and belly)

429-706-048-101

1st Quarter 2010

10.0

4.5

Emergency Egress (jettisonable crew doors and push-out passenger windows)

429-706-048-109

1st Quarter 2010

TBD

TBD

Tail-Rotor Guard

429-706-066-101

4th Quarter 2009

12.0

5.4

429-706-045-101



2.5

1.1

3rd Display Unit & Standby Compass (Required for Dual Pilot IFR)

429-706-026-101



23.6

10.7

ADF (Honeywell KR 87)

429-706-043-101

4th Quarter 2009

7.9

3.6

GNS-530 NAV/COMM/GPS (replaces Standard Equipment #1 GNS-430)

429-706-021-101



2.2

1.0

TCAS (Ryan 9900BX)

429-706-017-101

1st Quarter 2010

9.3

4.2

4th Axis Autopilot

429-706-703-103

1st Quarter 2010

4.5

2.0

Weather Radar (Primus 660)

429-706-018-101

1st Quarter 2010

24.4

11.1

Available as customized installation



4.3

2.0

429-706-047-101



1.4

0.6

Kit Description Optional Accessory Kits: AIRFRAME

AUDIO Aft Cabin ICS - 6 Place (Headsets not included) AVIONICS 1

ENGINE Engine Fuel Heater (PW207D2 Engine) (P&W) Compressor Wash Kit

Specifications subject to change without notice. Rev. 1 - September 2009

14

Bell 429 Product Specification

Optional Accessory Kits (con’t) Kit Description

Part Number

Projected Availability Status

Wt (lbs)

Wt (kg)

Notes

ENVIRONMENT 87.0

39.5

2, 3

429EC-200-1

 

113.3

51.4

2, 3

Single Evaporator Air Conditioning with Auto. Climate Control System and Bleed Air Heater

TBD

1st Quarter 2010

TBD

TBD

2, 3

Dual Evaporator Air Conditioning with Auto. Climate Control System and Bleed Air Heater

TBD

1st Quarter 2010

TBD

TBD

2, 3

429H-238-1



21.1

9.6

4, 6

Single Evaporator Air Conditioning with manual controls

429EC-202-1

Dual Evaporator Air Conditioning with manual controls

Bleed Air Heater Equipment EQUIPMENT Cargo Hook Provisions

429-706-009-103

1st Quarter 2010

11.3

5.1

Cargo Hook Equipment, 3,000 lb. capacity

429-706-009-101

1st Quarter 2010

29.0

13.2

429-604-001

4th Quarter 2009

N/A

N/A

High Gross Weight Towing kit Main Rotor Blade Folding Kit (1-fwd, 3 - aft)

429BF-900-1

1st Quarter 2010

1.0

0.5

Rescue Hoist Provisions

429-705-005-101

1st Quarter 2010

36.1

16.4

Rescue Hoist Equipment, 600 lb. capacity (Certified to Human External Cargo Standards)

429-706-001-101

1st Quarter 2010

182.0

82.6

429-706-058-101

1st Quarter 2010

14.1

6.4

429-260-001

2nd Quarter 2010

18.0

8.2

NVG Cockpit Lighting (US ITAR Controlled)

429-706-022-101

2nd Quarter 2010

2.0

0.9

NVG 3rd Display & Standby Compass (US ITAR Controlled)

429-706-022-103

2nd Quarter 2010

TBD

TBD

Corporate Interior

429-706-201-103



3.7

1.7

Headliner with LED lights & adjustable Air Conditioning vents

429-706-202-103



21.5

9.8

2

Corporate Headliner with adjustable Air Conditioning vents and colour coordinated leather trim

429-706-202-105



22.3

10.1

2

Carpets (for use with Dual Pilot Controls)

429-706-033-101

4th Quarter 2009

20 to 28

9.1 to 12.7

Carpets (for use with Single Pilot Controls)

429-706-033-103

4th Quarter 2009

20 to 28

9.1 to 12.7

Soundproofing - Standard (light weight)

429-706-034-101

3rd Quarter 2009

10.0

4.5

5

Soundproofing - Enhanced

429-706-034-103

3rd Quarter 2009

35.0

15.9

5

Aft Cabin Bulkhead Closeout panel

429-706-060-101

3rd Quarter 2009

46.0

20.9

5, 6

Available as customized installation

4th Quarter 2009

-20.0

-9.1

FLIGHT & ENGINE INSTRUMENTS Cockpit Voice Recorder/Flight Data Recorder, crashworthy Health & Usage Monitoring System

INTERIOR

Utility Light Weight Interior

Note: All interior option weight values are delta increase or decrease from standard configuration weights. PASSENGER SEATING OPTIONS Standard Seating - 6-Place, Standard 15.5” seats with 4-point restraint system, quick release disconnects & ICS fixed provisions

429-706-010-117



127.4

57.8

Standard Wide Seating – 6-Place, Standard 18.5” wide seats with 4-point restraint system, quick release disconnects & ICS fixed provisions

429-706-010-103



140.6

63.8

Specifications subject to change without notice. Bell 429 Product Specification

15

Rev. 1 - September 2009

Optional Accessory Kits (con’t) Part Number

Projected Availability Status

Wt (lbs)

Wt (kg)

Corporate 6-Place Seating, 18.5” wide seats with 3-point restraint system, quick release disconnects & ICS fixed provisions

429-706-010-105



156.9

71.2

Corporate 5-Place club seating with 1 centre console and side arm rests, 3-point restraint system, quick release disconnects & ICS fixed provisions

429-706-010-107

4th Quarter 2009

174.4

79.1

Corporate 4-Place club seating with centre consoles and side arm rests, 3-point restraint system, quick release disconnects & ICS fixed provisions

429-706-010-109

4th Quarter 2009

174.2

79.0

High Visibility Crew Door Window L/H (Bulged Window)

429-574-101

1st Quarter 2010

2.0

0.9

High Visibility Crew Door Window R/H (Bulged Window)

429-574-102

1st Quarter 2010

2.0

0.9

High Visibility Forward Passenger Door Window L/H (Bulged Window)

429-582-101

1st Quarter 2010

4.0

1.8

High Visibility Forward Passenger Door window R/H (Bulged Window)

429-582-102

1st Quarter 2010

4.0

1.8

Sliding Window modification for Sliding Passenger Door L/H

429-564-101

1st Quarter 2010

4.4

2.0

Sliding Window modification for Sliding Passenger Door R/H

429-564-102

1st Quarter 2010

4.4

2.0

High Visibility Window for Sliding Passenger Door L/H

429-583-101

1st Quarter 2010

4.0

1.8

High Visibility Window for Sliding Passenger Door R/H

429-583-102

1st Quarter 2010

4.0

1.8

Automatic Door Openers, Crew (2 door kit)

429-510-001

4th Quarter 2009

2.0

0.9

Automatic Door Openers, Passenger (2 door kit)

429-510-002

4th Quarter 2009

2.2

1.0

965-42901-011

4th Quarter 2009

18.5

8.4

Kit Description

Notes

VENDOR KITS – STC

Wire Strike Protection System Detachable Equipment, skid gear a/c RECOMMENDED

8

Optional Accessories Explanatory Notes 1.

Kits required for Dual Pilot IFR

2.

Headliner with adjustable air conditioning vents, p/n 429-706-202-103 or 429-706-202-105, is recommended for more effective cooling when air conditioning is installed.

3.

Air Conditioning Quill Drive and Fixed Provisions are included in Standard Configuration.

4.

Heater Provisions are included in Standard Configuration.

5.

Installation of soundproofing requires installation of the Aft Cabin Bulkhead panel.

6.

Standard Heater Equipment requires installation of the Aft Cabin Bulkhead panel.

7.

EMS Heater Equipment outlets are configured to accommodate aircraft in which the Aft Cabin Bulkhead panel is not installed.

8.

Wire Strike Protection System Provisions are included in Standard Configuration.

Specifications subject to change without notice. Rev. 1 - September 2009

16

Bell 429 Product Specification

FUEL FLOW CHARTS ISA & ISA+20OC NEW PRATT & WHITNEY CANADA PW207D1/D2 ENGINES BASIC INLET OR BARRIER FILTER INSTALLED CLEAN CONFIGURATION WITH STANDARD SKID GEAR AIR CONDITIONING / HEATER OFF

Bell 429 Product Specification

17

Rev. 1 - September 2009

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = Sea Level OAT = 15OC (ISA) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680 100

640

290

95

620

280

90

600

270

580

85

45

220

460

210

440

200 MAX ENDUR.

420 400 380

40

360

35

340

30

320

70 65 60 55 50

190

LB

50

480

10 0

55

230

500

180 VNE

170

x

60

240

520

160

W

65

250

G

70

260

540

FUEL FLOW - LB/HR

75

LRC

560

80

TORQUE - %

300

TRANSMISSION LIMIT

FUEL FLOW - KG/HR

660

150 140

300

130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40 50 60 70 80 90 100 110 120 130 140 150 160 170 INDICATED AIRSPEED - KNOTS

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 Rev. 1 - September 2009

18

Bell 429 Product Specification

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 2000 Ft OAT = 11OC (ISA) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680 300

660

95 90

280

600

270

580 560

80

540

45 40 35 30

480

220

460

210

440

200

420 400 380 360 340 320

190

MAX ENDUR.

70 65 60 55 50

180

LB

50

230

500

VNE

170

10 0

55

240

520

160

x

60

250

W

65

260

LRC

150

G

70

FUEL FLOW - LB/HR

TORQUE - %

620

85

75

290

FUEL FLOW - KG/HR

640

100

TRANSMISSION LIMIT

140

300

130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40 50 60 70 80 90 100 110 120 130 140 150 160 170 INDICATED AIRSPEED - KNOTS

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 Bell 429 Product Specification

19

Rev. 1 - September 2009

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 4000 Ft. OAT = 7OC (ISA) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680 300

660

620

95

280

600

270

90

580

50

460

210

440

200

420

190

400 380

45

360

40

340

35

320

30

300

180

MAX ENDUR.

70 65 60 55 50

VNE

170 160

LB

55

220

10 0

60

480

150

x

65

230

500

W

70

240

LRC

520

140

G

75

250

540

FUEL FLOW - LB/HR

80

260

560

85

TORQUE - %

290

TRANSMISSION LIMIT

FUEL FLOW - KG/HR

640

100

130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40 50 60 70 80 90 100 110 120 130 140 150 160 INDICATED AIRSPEED - KNOTS

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 Rev. 1 - September 2009

20

Bell 429 Product Specification

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 6000 Ft OAT = 3OC (ISA) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680 300

660

620 600

95

80

520

40 35 30

240

500

230

LRC

480

220

460

210

440

200

420

190

400

180 MAX ENDUR.

380

340 320 300

70

6 65 550 50

170 160

LB

360

VNE

150

10 0

45

250

x

50

260

140

W

55

270

G

60

FUEL FLOW - LB/HR

TORQUE - %

540

65

MAX CONTINUOUS POWER

560

85

70

280

580

90

75

290

TRANSMISSION LIMIT

FUEL FLOW - KG/HR

640

100

130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40 50 60 70 80 90 100 110 120 130 140 150 160 INDICATED AIRSPEED - KNOTS

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 Bell 429 Product Specification

21

Rev. 1 - September 2009

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 8000 Ft. OAT = -1OC (ISA) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680

95

270

250 240

520

230

500 480

220

460

210

440

200

420

190

400

180

380

45

340

40

320

35

300 280

MAX ENDUR.

LRC

70

65 60 55 50

170 160 150

LB

360

VNE

10 0

50

30

260

MAX CONTINUOUS POWER

140

x

55

600

W

60

280

130

G

65

620

540

FUEL FLOW - LB/HR

TORQUE - %

70

290

560

85

75

640

580

90

80

300

FUEL FLOW - KG/HR

100

660

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40

50

60 70 80 90 100 110 120 130 140 150 INDICATED AIRSPEED - KNOTS

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 Rev. 1 - September 2009

22

Bell 429 Product Specification

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 10,000 Ft OAT = -5OC (ISA) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680

95

290

620

280

600

270 260

560

250

540

FUEL FLOW - LB/HR

85

MAX CONTINUOUS POWER

240

520

230

500 480

220

460

210

440

200

420

190

60

400

180

55

380

50

360

45 40 35 30

VNE

MAX ENDUR.

340

65

300

60 55 50

280 260

160

LRC

70

320

170

150

LB

65

140

10 0

70

130

x

75

G W

TORQUE - %

640

580

90

80

300

FUEL FLOW - KG/HR

100

660

120

40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40

50

60 70 80 90 100 110 120 130 140 150 INDICATED AIRSPEED - KNOTS

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 Bell 429 Product Specification

23

Rev. 1 - September 2009

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = Sea Level OAT = 35OC (ISA+20OC) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680

640

95 90

35 30

240

520

230

500 480

220

460

210

440

360 340

190 180

LB

380

70 65 60 55 50

10 0

400

MAX ENDUR.

VNE

170

x

420

200

LRC

160

W

40

250

G

45

FUEL FLOW - LB/HR

50

260

540

75

TORQUE - %

270

80

55

290

600

560

60

MAX CONTINUOUS POWER

280

580

65

300

620

85

70

TRANSMISSION LIMIT

FUEL FLOW - KG/HR

660

100

150

320

140

300

130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40 50 60 70 80 90 100 110 120 130 140 150 160 170 INDICATED AIRSPEED - KNOTS

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 Rev. 1 - September 2009

24

Bell 429 Product Specification

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 2000 Ft OAT = 31OC (ISA+20OC) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680 660

300

640

290

95

620

280

90

600

480

220

460

210

440

200

420

40

360

35

340

30

320

70 65 60 55 50

LB

380

LRC

180 VNE

170

10 0

400

45

190

MAX ENDUR.

160

x

50

230

500

W

55

240

520

150

G

60

250

540

FUEL FLOW - LB/HR

TORQUE - %

65

260

560

80

70

270

580

85

75

MAX CONTINUOUS POWER

FUEL FLOW - KG/HR

100

140

300

130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40 50 60 70 80 90 100 110 120 130 140 150 160 INDICATED AIRSPEED - KNOTS

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 Bell 429 Product Specification

25

Rev. 1 - September 2009

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 4000 Ft. OAT = 27OC (ISA+20OC) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680 660

300

100

640

290

95

620

280

600

270

80

540

50 45 40

480

220

460

210

440

200

420

190 MAX ENDUR.

400 380 360 340

35

320

30

300

LRC

70

65 60 55 50

180 VNE

170

LB

55

230

500

160

10 0

60

240

520

150

x

65

250

W

70

260

MAX CONTINUOUS POWER

FUEL FLOW - KG/HR

560

FUEL FLOW - LB/HR

85

75

TORQUE - %

580

G

90

140 130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40 50 60 70 80 90 100 110 120 130 140 150 160 INDICATED AIRSPEED - KNOTS

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 Rev. 1 - September 2009

26

Bell 429 Product Specification

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 6000 Ft OAT = 23OC (ISA+20OC) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680

290

620

280

600

270

580

85

560 540

480

220

460

210

440

200

420

190

55

400

50

380

45

360

40 35 30

230

500

180

MAX ENDUR.

LRC

VNE

170

70

340

65 60 55 50

320 300

160

LB

60

240

520

150

10 0

65

250

MAX CONTINUOUS POWER

x

70

FUEL FLOW - LB/HR

75

260

FUEL FLOW - KG/HR

90

80

TORQUE - %

640

140

W

95

300

G

100

660

130

280

120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40

50

60 70 80 90 100 110 120 130 140 150 INDICATED AIRSPEED - KNOTS

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 Bell 429 Product Specification

27

Rev. 1 - September 2009

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 8000 Ft. OAT = 19OC (ISA+20OC) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680

95

45

260 250 240

520

MAX CONTINUOUS POWER

500

230

480

220

460

210

440

200

420

190

400 380 360

320

35

300

30

280

VNE

65

60 55 50

170

LRC

70

340

40

180

MAX ENDUR.

160

LB

50

270

150

10 0

55

600

140

x

60

280

G W

65

620

540

FUEL FLOW - LB/HR

TORQUE - %

70

290

560

85

75

640

580

90

80

300

FUEL FLOW - KG/HR

100

660

130 120

260 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40

50

60 70 80 90 100 110 120 130 140 150 INDICATED AIRSPEED - KNOTS

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 Rev. 1 - September 2009

28

Bell 429 Product Specification

Fuel Flow vs Airspeed New Engines Clean Configuration with Standard Skid Gear Engine RPM - 100% Zero Wind Pressure Altitude = 10,000 Ft OAT = 15OC (ISA+20OC) TRUE AIRSPEED - KM/HR 80 100 120 140 160 180 200 220 240 260 280 300 320 680

95

300

640

290

620

280

600

270

580

90

260

560 85

75 70 65 60 55

FUEL FLOW - LB/HR

TORQUE - %

80

480

220

MAX CONTINUOUS POWER

460

210

440

200

420

190

400

45

180

MAX ENDUR.

380

340

30

230

500

360

35

240

520

50

40

250

540

VNE

170 160

70

65

320

60

300

55 50

280

FUEL FLOW - KG/HR

100

660

W G

260

x

0 10

LB

150

LRC

140 130 120

40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 TRUE AIRSPEED - KNOTS 40

50

60 70 80 90 100 110 120 130 140 INDICATED AIRSPEED - KNOTS

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 Bell 429 Product Specification

29

Rev. 1 - September 2009

PERFORMANCE CHARTS IGE & OGE HOVER AND SERVICE CEILINGS PRATT & WHITNEY CANADA PW207D1/D2 ENGINES MINIMUM SPECIFICATION ENGINE POWER BASIC INLET OR BARRIER FILTER INSTALLED AIR CONDITIONING / HEATER OFF

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 Rev. 1 - September 2009

30

Bell 429 Product Specification

IGE Hover Ceiling Twin Engine Takeoff Power Basic Inlet or Barrier Filter Installed Rotor RPM = 100% Zero Wind or Headwind

GROSS WEIGHT - 100 KG 21

22

23

24

25

20 C 0° +3

°C 20 A+ IS

A IS

19

IS

26 A+ 10 °C

27

28

29

30

31

32

33

34 60

IS A

56

18

52

17 -40 °C -30 °C -20 °C

14

44 40

13 12

0° C

AX M

36

O AT

11

IT M LI

20 °C

(IS

10

. 36 A+

30 °

10 °C

32

C

28

C 7°

9

)

PRESSURE ALTITUDE - 1000 FT

15

48

8

24

7

20

6

40 °C

16

3 2

SKID HEIGHT 4 FT (1.2M)

1 0

MAX EXT GW 7500 LBS

4

MAX INT GW 7000 LBS

5

PRESSURE ALTITUDE - 100 METERS

-1 0° C

16

12 8 4 0

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74 76

GROSS WEIGHT - 100 LB

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 Bell 429 Product Specification

31

Rev. 1 - September 2009

OGE Hover Ceiling Twin Engine Takeoff Power Basic Inlet or Barrier Filter Installed Rotor RPM = 100% Zero Wind or Headwind

GROSS WEIGHT - 100 KG 22

23

24

25

26

27

28

29

30

31

32

33

34

MAX INT GW 7000 LBS

A IS

°C 20

°C 10 A+ IS

A+ IS

19

MAX EXT GW 7500 LBS

20

18 17 16

60 56 52 48

15 44

3 A+

-4 0°

C

13

-3 0°

C

12

-2 0°

C

-1 0°

C

C 0° AX M AT O

11

0°

LI

10

M IT (IS

10

C

°C

40 36 32

36 A+

28

.7

9

) °C

PRESSURE ALTITUDE - 1000 FT

IS

14

8

24 20

7 30

6

40 °C

5

°C

20 °C

16

4

PRESSURE ALTITUDE - 100 METERS

21

12

3

8

2 4

1 0

0 46 48 50 52 54 56 58 60 62 64 66 68 70 72 74 76

GROSS WEIGHT - 100 LB

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 Rev. 1 - September 2009

32

Bell 429 Product Specification

OEI Service Ceiling OEI 30-Minute Power Basic Inlet or Barrier Filter Installed Zero Wind or Headwind

GROSS WEIGHT - 100 KG 21

22

23

24

25

26

27

28

29

30

31

20

60

18 17 16

°C

°C 20

°C 10 A+ IS

A+ IS

0 +3

14

A IS

12 11

10 °C

AT O

0° C

-4 0° C -3 0° C -2 0° C -1 0° C

IT ) °C .7 36 A+

8

40 36 32 28

(IS

9

48

M LI

10

52

44 IS A

13

AX M

PRESSURE ALTITUDE - 1000 FT

15

56

20 °C

7

30 °C

6 40

5

°C

4

24 20 16

PRESSURE ALTITUDE - 100 METERS

MAX INT GW 7000 LBS

19

12

3

8

2 4

1 0

0 46 48 50 52 54 56 58 60 62 64 66 68 70

GROSS WEIGHT - 100 LB

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 Bell 429 Product Specification

33

Rev. 1 - September 2009

OEI Service Ceiling OEI Max Continuous Power Basic Inlet or Barrier Filter Installed Zero Wind or Headwind

GROSS WEIGHT - 100 KG 21

22

23

24

25

26

27

28

29

30

31

20

60 MAX INT GW 7000 LBS

18 17 16

-3 0° C

10 °C

10

32

-1 0° C

28 24

LI IT M

20 °C

. 36 A+ (IS C) 7°

5

0° C

T OA

6

36

-2 0° C

AX

7

40

M

PRESSURE ALTITUDE - 1000 FT

-4 0° C

11

8

48 44

12

9

52

A IS

C

C 0°

° 30 A+ IS

13

2 A+ IS

14

°C 10 A+ IS

15

56

20

30 °C

16

4

PRESSURE ALTITUDE - 100 METERS

19

12

3

40

2

8

°C

4

1

50 °C

0

0 46 48 50 52 54 56 58 60 62 64 66 68 70

GROSS WEIGHT - 100 LB

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 Rev. 1 - September 2009

34

Bell 429 Product Specification

Service Ceiling Twin Engine Max Continuous Power Basic Inlet or Barrier Filter Installed Zero Wind or Headwind

GROSS WEIGHT - 100 KG 20 19 18 17

22

23

24

25

26 IS A+ 30 °C M

AX

16 15

PRESSURE ALTITUDE - 1000 FT

27

O AT

28 IS A+ 20

29

30

IS A °C

-20 °

+1 0

-10

31 C

-30 °C

IS

A

°C

56

°C 0° C

LI M

IT

(IS A+

52

10 °C 36 .7 °

20 C

60

48

°C

)

44

14 13

40

12

36

11

32

10 9

28

8

24

7

20

6 16 MAX INT GW 7000 LBS

5 4 3 2 1 0

PRESSURE ALTITUDE - 100 METERS

21

12 8 4 0

46 48 50 52 54 56 58 60 62 64 66 68 70

GROSS WEIGHT - 100 LB

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 Bell 429 Product Specification

35

Rev. 1 - September 2009

Page Intentionally Left Blank

Rev. 1 - September 2009

36

Bell 429 Product Specification

Bell 429 Product Specification

37

Rev. 1 - September 2009

P.O. Box 482, Fort Worth, Texas 76101 Phone: 817-280-2800 Fax: 817-278-8802 www.bellhelicopter.com Bell Helicopter Textron Canada Limited 12,800 rue de l’ Avenir Mirabel, Quebec, Canada J7J1R4 Phone: 450-437-3400 Fax: 450-437-2006 ©2009 Bell Helicopter Textron Inc. All Rights Reserved. Printed in USA July 2009