PRODUCT SPECIFICATIONS JANUARY 2005
For additional information visit the Bell Helicopter Textron Textron Website Website Homepage: www.bellhelicopter.com
Sales Contact Telephone Numbers Sales Inquiries U.S. Toll Free: 800 800-FLY -FLY-BE -BELL LL 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 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
For additional information visit the Bell Helicopter Textron Textron Website Website Homepage: www.bellhelicopter.com
Sales Contact Telephone Numbers Sales Inquiries U.S. Toll Free: 800 800-FLY -FLY-BE -BELL LL 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 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 intende d 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 employ employees, ees, and BHTI independen independentt 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. configuration s. Please consult the NOTES found in the right margins of the optional equipment list pages for equipment compatibility. 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.
©C op yr ig ht , Be ll He l ic op te r Te xt ro n, In c. , 20 05
Product Specifications
®™ , Be ll He li co pt er , Be ll He li co pt er Te xt ro n In c. , Be ll 206B3, 206L-4, 407, 427, 430, 412, 609, JetRanger and LongRanger are registered trademarks of Bell Helicopter Textron Inc.
1
427VFR January 2005
EXTERIOR DIMENSIONS STANDARD LOW SKID GEAR 427 STD GEAR
0.9 FT (0.27 m)
13.4 FT (4.09 m)
37.5 FT (11.42 m) 18.5 FT (5.64 m)
8.8 FT (2.68 m)
0.6 FT (0.19 m)
5° MAST TILT
2° PRECONE FLA P 6° 6° UP
Ø 5.7 FT (1.73 m)
STATIC DROOP (BOTH SIDES)
FLAP 6° DN
10.5 FT (3.20 m) 6.4 FT (1.94 m)
8.3 FT (2.53 m)
6.1 FT (1.86 m)
1.3 FT (0.40 m)
6.0 FT (1.84 m)
16.0 FT (4.87 m)
22.1 FT (6.73 m)
STATIC GROUND LINE AT MAX GW 6550 LB (2971 K G) MID CG
10.0 FT (3.04 m)
36.5 FT (11.13 m) 42.6 FT (12.99 m)
OPTIONAL HIGH SKID GEAR w/AAI FLIGHTSTEP ®
13.4 FT (4.09 m)
427 HIGH SKID GEAR
3.3 FT (1.01 m)
0.9 FT (0.27 m)
1.2 FT (0.36 m) 37.5 FT (11.42 m) 18.5 FT (5.64 m)
8.8 FT (2.69 m)
5° MAST TILT
2° PRECONE
0.6 FT (0.19 m)
FLA P 6° UP STATIC DROOP (BOTH SIDES)
FLA P 6° DN
Ø 5.7 FT (1.73 m)
11.4 FT (3.48 m) 1.5 FT (0.45 m)
8.8 FT (2.67 m)
2.2 FT (0.66 m)
7.2 FT (2.18 m)
6.1 FT (1.87 m)
6.0 FT (1.82 m)
10.0 FT (3.05 m) 10.0 FT (3.05 m) 16.0 FT (4.86 m)
22.0 FT (6.73 m)
4.2 FT (1.29 m)
STATIC GROUND LINE AT MAX GW 6550 LB (2971 KG) MID CG
36.5 FT (11.13 m)
42.6 FT (13.00 m)
Product Specifications
Specifications subject to change without notice. 2
427VFR January 2005
OPTIONAL EMERGENCY FLOAT GEAR w/ AAI FLOATSTEP ® 0.9 FT (0.27 m)
13.4 FT (4.09 m)
427 WITH FLOAT KIT
1.2 FT (0.36 m) 37.5 FT (11.42 m) 18.5 FT (5.64 m)
8.8 FT (2.69 m)
5° MAST TILT
2° PRECONE
0.6 FT (0.19 m)
FLAP 6° UP
Ø 5.7 FT (1.73 m)
STATIC DROOP (BOTH SIDES)
FLAP 6° DN
11.4 FT (3.48 m) 1.4 FT (0.42 m)
1.2 FT (0.38 m) 9.0 FT (2.73 m)
2.2 FT (0.66 m)
7.2 FT (2.18 m)
3.5 FT (1.06 m) 6.1 FT (1.87 m)
4.2 FT (1.29 m) 10.0 FT (3.04 m) 19.6 FT (5.98 m)
16.1 FT (4.92 m)
STATIC GROUND LINE AT MAX GW 6550 LB (2971 K G) MID CG
36.5 FT (11.13 m)
25.7 FT (7.84 m) 42.6 FT (13.00 m)
OPTIONAL BLADE FOLDING KIT DIMENSIONS
8.3 FT (2.52 m)
42.8 FT (13.03 m)
MINIMUM HANGAR SIZE* ROTOR NOT FOLDED 30.0 FT X 40.0 FT [ 9.0 M X 12.0 M ] MINIMUM HANGAR SIZE* ROTOR FOLDED 8.3 FT X 42.8 FT [ 2.6 M X 13.1 M ] *ALLOWANCE SHOUL D BE MADE FOR HIGH SKID GEAR, GROUND WHEELS, EMPTY FUEL CONDITION, AND DOOR LIP WHEN CONSIDERING HANGAR DOOR WIDT H AND HEIGHT
Product Specifications
Specifications subject to change without notice. 3
427VFR January 2005
INTERNAL DIMENSIONS PASSENGER CABIN FLOOR SPACE WITH SEATS REMOVED [APPROXIMATE]
Approximate cargo space: Aft Cabin - 2.9 cubic meters (102 cubic feet) Left front - 0.6 cubic meters (20 cubic feet) Baggage compartment-0.76 cubic meters (27 cubic feet) Max Floor Loading: Aft Cabin - 366 kg/M 2 (75 lb/ft 2 ); Maximum internal load -600 kg (1313 lb) Baggage Compartment - 420 kg/M 2 (86 lb/ft 2 ); Max Baggage weight-113 kg (250 lb)
Product Specifications
4
427VFR January 2005
PASSENGER CABIN DOOR DIMENSIONS
Product Specifications
5
427VFR January 2005
SPECIFI CATION SUM MARY (U. S. Units) WEIGHTS
(Serial No. 56047 & Subsequent)
LBS
Standard Configuration Weight (Note 1) Normal Gross Weight (Note 2) External Gross Weight Standard Configuration Useful Load (Normal Gross Wt - Standard Configuration Wt) Maximum External Load (Cargo Hook Limit)
3881 6350/6550 6550 2469/2669 3000
Note 1: Includes twenty-five pounds of engine oil. Ballast is not included in standard configuration weight (ballast is function of installed equipment). Note 2: Alternate Maximum Gross Weight of 6550 lbs (2971kg) is permitted when operating within the limitations of FAA Approved Rotorcraft Flight Manual Supplement BHT-427-FMS-7.
PERFORMANCE SUMMARY: • • • REFER TO DEMONSTRATED TAKEOFF & LANDING AND MAXIMUM OPERATING ALTITUDE NOTES ON THE PERFORMANCE CHARTS • • • (Note 2)
TAKEOFF, GROSS WEIGHT IGE Hovering Ceiling
LBS ISA ft ISA+20C ft OGE Hovering Ceiling ISA ft ISA+20C ft Service Ceiling (MCP) - AEO ISA ft ISA+20C ft (30 minute) - OEI ISA ft ISA+20C ft No Height-Velocity Ceiling (Note 3) ISA ft ISA+20C ft Cruise @ Sea Level ISA Maximum Cruise Speed kn Long Range Cruise Speed (avg GW) kn Range @LRC, No Reserve nm Endurance @ Loiter 60 kn ISA, SL hr (no reserve)
5000 9000 6729 10,000 10,000 10,000 10,000 10,000 10,000
5500 9000 6729 10,000 10,000 10,000 10,000 10,000 10,000
7000 4728
7000 4728
143 131 338
142 133 400
6000 9000 6729 10,000 9300 10,000 10,000 10,000 9450
6350 9000 6729 6000 3700 10,000 10,000 8000 6050
6550 9000 6729 1750 ([email protected]) 10,000 10,000 4600 2500
4080 2135 ([email protected]) 1810 ([email protected]) n/a 140 134 394
138 134 390
136 133 387 4.0
Note 3: Height-Velocity has been demonstrated up to 7000 ft Density Altitude per FAR Part 27.
ENGINE RATINGS:
Uninstalled Thermodynamic Shaft Horsepower
Pratt & Whitney Canada PW207D with Full Authority Digital Electronic Control (FADEC). Takeoff (5 Minutes) SHP Maximum Continuous SHP OEI (30 seconds) SHP OEI (2 minute) SHP OEI (30 minute) SHP OEI (Continuous) SHP TRANSMISSION RATING: Takeoff (5 Minutes) AEO Continuous AEO 30 Second OEI 2 Minute OEI Continuous OEI
710 625 820 780 750 710
SHP SHP SHP SHP SHP
FUEL CAPACITY (USABLE): Standard
Engine Rated Shaft Horse- power
550 550 650 650 550 550
800 800 650 605 460
203.5 US 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
427VFR January 2005
SPECIFICATION SUMMARY (Metri c Unit s) WEIGHTS
(Serial No. 56047 & Subsequent)
KG
Standard Configuration Weight (Note 1) Normal Gross Weight (Note 2) External Gross Weight Std. Conf. Useful Load (Normal Gross Wt - Standard Configuration Wt) (Note 2) Maximum External Load (Cargo Hook Limit)
1760 2880/2971 2971 1120/1211 1361
Note 1: Includes eleven kilograms of engine oil. Ballast is not included in standard configuration weight (ballast is function of installed equipment). Note 2: Alternate Maximum Gross Weight of 6550 lbs (2971kg) is permitted when operating withthe limitations of FAA Approved Rotor- craft Flight Manual Supplement BHT-427-FMS-7.
PERFORMANCE SUMMARY: • • • REFER TO DEMONSTRATED TAKEOFF & LANDING AND MAXIMUM OPERATING ALTITUDE NOTES ON THE PERFORMANCE CHARTS • • • (Note 2)
TAKEOFF, GROSS WEIGHT IGE Hovering Ceiling
KG m m m m m m m m
ISA ISA+20C OGE Hovering Ceiling ISA ISA+20C Service Ceiling (MCP) - AEO ISA ISA+20C (30 minute) - OEI ISA ISA+20C No Height-Velocity Ceiling (Note 3) ISA m ISA+20C m Cruise @ Sea Level ISA Maximum Cruise Speed km/h Long Range Cruise Speed (avg GW) km/h Range @LRC, No Reserve km Endurance @ Loiter 111 km/h ISA, SL hr (no reserve)
2268 2743 2051 3048 3048 3048 3048 3048 3048
2495 2743 2051 3048 3048 3048 3048 3048 3048
2722 2743 2051 3048 2835 3048 3048 3048 2880
2134 1441
2134 1441
1244 651 ([email protected]) 552 ([email protected]) n/a
265 243 626
263 246 741
259 248 730
2880 2971 2743 2743 2051 2051 1829 533 1128 ([email protected]) 3048 3048 3048 3048 2438 1402 1844 762
256 248 722
251 246 716 4.0
Note 3: Height-Velocity has been demonstrated up to 2134 M Density Altitude per FAR Part 27.
ENGINE RATINGS:
Uninstalled Thermodynamic Power
Pratt & Whitney Canada PW207D with Full Authority Digital Electronic Control (FADEC). Takeoff (5 Minutes) kW Maximum Continuous kW OEI (30 seconds) kW OEI (2 minute) kW OEI (30 minute) kW OEI (Continuous) kW TRANSMISSION RATING: Takeoff (5 Minutes) AEO Continuous AEO 30 Second OEI 2 Minute OEI Continuous OEI
529 466 611 582 559 529
kW kW kW kW kW
FUEL CAPACITY (USABLE): Standard
Engine Rated Power
410 410 485 485 410 410
597 597 485 451 343
770 Liters
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
7
427VFR January 2005
427 SEATING CREW SEATING - Two individual ergonomically designed energy attenuating seats with adjustable lumbar sup- port, 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. The seat belt straps are black, with silver metal fasteners.
STANDARD EIGHT PLACE SEATING
STANDARD SEATING AND INTERIOR TRIM The standard configuration cabin seating is the traditional club format of two rows of three energy attenuating seats, with individual seat belts and single strap shoulder harness, arranged facing each other. Available with Grey, Blue, Red, or Tan fabric upholstery with Black seat bel ts (crew and passengers). Seats are upholstered in fabric or
at extra cost in all vinyl, with painted seat frames. Th e standard interior trim consists of full plastic closeouts on all airframe areas, vinyl covered arm rests, and molded plastic headliners. The floor is covered in a durable low loop Nylon blend carpet. The standard seating and interior trim are included in the standard configuration aircraft weight.
OPTIONAL CORPORATE CLUB SEATING
Specifications subject to change without notice.
Product Specifications
8
427VFR January 2005
OPTIONAL CORPORATE CLUB SEATS AND INTERIOR TRIM Corporate seating is available with main cabin club seating arrangements for four or five passengers (all passenger seats are energy attenuating) . Five passenger cabin arrangements include either three rear facing/two forward facing seats, or two rear facing/three forward facing seats. All tw o seat modules include a center storage console* . The “Contoured Style” seats have leather covered side frames and are available with Pewter,
Mushroom, Dark Blue, Saddle, Burgundy, Smoke Grey, and Forest Green upholstery and color coordinated seat belts with silver metal fasteners (Crew seat belt straps are black). Seats can be either all fabric or all leather. The corporate interior trim consists of full plastic closeouts on all airframe areas, door pockets, and lower cabin sidewalls covered with color coordinated leather. Carpet is richly textured 100% wool cut pile.
* Any center storage console may be deleted from one of the Corporate Configurations to allo w for
the Customized installation of a Refreshment Center or an Entertainment System.
Specifications subject to change without notice.
Product Specifications
9
427VFR January 2005
Standard Configuration (Items Included in List Price) Engine Air Particle Separators w/Bleed Air Lines Fuselage, all composite exterior shell and internal Engine Wash lines / equipment bulkheads of graphite and nomex honeycomb Fire Detector and Extinguisher system construction (with aluminum honeycomb roof panel) Fuel Heater (no anti-ice additive required) attached to dual external main roof beams of 7050 Full authority digital electronic control (FADEC) aluminum alloy (connecting the fuselage to the {Electronic Engine Control-Hamilton Standard} transmission) {Fuel Management Module-Woodward Fairings, all composite graphite and nomex honeycomb Governor} or BMI thermoplastic aerodynamic fairings for the OEI Training Mode flight controls, transmission, engine, and tail rotor Dual feed interconnected fuel system: driveshafting and tail rotor gearbox cover 203.5 US gallons (770 liters) of usable fuel in 3 Doors (four), two for pilot & passengers on right side, crash-resistant cells (with electrically two for copilot and passengers on left side, all doors controlled interconnect valve). of composite material Each feed tank is supplied by a transfer pump. Baggage compartment (27 ft 3 /0.76M 3 , 250 lbs/113 Kg Engines are supplied by engine mounted capacity), with composite door (on the right side of suction pumps. Each of the three tanks has a aft fuselage) remote push-button fuel sump drain. Locks for cabin doors and baggage compartment Automatic Fuel Burn Management System Landing gear, tubular aluminum skid type with Manual fuel shutoff system replaceable skid shoes TRANSMISSION AND DRIVE SYSTEMS Provisions for mooring, jacking and single point lifting Fuselage Mounted Maintenance Steps and Step/ One 2 stage (dual spiral-bevel engine inputs, with a single Handgrips helical collector gear) 15.18 :1 speed reduction Tail boom, monocoque aluminum structure with transmission (capable of extended operation after loss aluminum honeycomb vertical fin and composite of lubrication) fixed horizontal stabilizer and auxiliary finlets Two fluid filled pylon mounts [LIVE] suspension [left and Tail skid (tail rotor guard) right vertical axis mounts) Windows, gray tinted plexiglass (windshields are clear Two elastomeric forward / aft restraints plexiglass) [sliding vent windows in main cabin Three main transmission chip detectors doors are available as a no-cost option] Internal wet-sump transmission lubrication with external Three color exterior paint schemes (3-color standard, oil cooler additional colors and special paint schemes priced One transmission-mounted hydraulic pump on request) One blank transmission drive pad ( provision for #2 hydraulic pump or accessory drive) INTERIOR Free-wheeling unit at each power input Segmented tail rotor driveshaft 8-place interior (STANDARD CLUB SEATING) with Single stage, bevel gear, 90 deg tail rotor gearbox with integral soundproofing, floor carpeting, and splash lubrication miscellaneous stowage. Color options available for One tail rotor gearbox chip detector upholstery and carpet Cockpit-2 energy attenuating seats with seat belts, dual ROTORS AND CONTROLS shoulder straps, and inertia reel Cabin-6 energy attenuating passenger seats with seat Pilot flight controls belts, single shoulder strap, and inertia reel Mechanical control linkages Fire extinguisher, (1) cockpit Adjustable friction controls on cyclic and collective First aid kit (Canadian Registered helicopters only) Adjustable antitorque pedals Floor covering throughout Single hydraulic system with separate pump, reservoir Parcel shelf behind rear row of cabin seats and filter with Ground test provisions Ram air ventilation system for cockpit and cabin Hydraulic Off Trim System [HOTS] for the (2) cyclic servos Composite soft-in-plane Main Rotor Hub Main rotor [4-bladed, fiberglass and nomex honeycomb POWER PLANT composite with stainless steel leading edge abrasion Two fully isolated Pratt & Whitney Canada PW207D strip] turboshaft engines with independent: Tail rotor [2-bladed, fiberglass composite with stainless Oil reservoir (integral to engine case) steel leading edge abrasion strip] Oil cooler Airspeed Activated Pedal Stop [AAPS] with built in test Titanium forward firewall function, electrical override release switch, and Titanium center firewall & T/R Driveshaft tunnel manual override release Titanium aft firewall
AIRFRAME
Titanium lower horizontal fireshields (L&R) Engine Fluid Containment Reservoirs (2)
Specifications subject to change without notice.
Product Specifications
10
427VFR January 2005
Standard Configuration (continued) INSTRUMENTS 1 electrically heated pitot/static system. Airspeed indicator (knots) Inclinometer Altimeter Vertical Speed Indicator Magnetic compass INTEGRATED INSTRUMENT DISPLAY SYSTEM (IIDS) incorporating: Triple torquemeter, engine 1 & 2, plus digital total, Triple tachometer Two measured gas temperature (MGT) indicators Two gas producer tachometers (NG) Transmission oil pressure and temperature indicator Two engine oil pressure and temperature indicators One dual ammeter Generator(2) and battery voltage (digital) Fuel quantity and totalizer Fuel temperature Caution/warning/advisory panel Clock Engine hourmeter (on time page) Outside air temperature indicator Maintenance functions, and power assurance checks Exceedance monitoring, warning, and recording OEI Training Mode
FADEC fail FADEC degraded Fuel Imbalance Fuel tank interconnect valve open Fuel temperature [high & low] (2) Fuel transfer (2) Fuel pressure low IIDS fail OEI flags Starter energized Transmission chips (3) Transmission oil temperature and pressure Pedal Stop Tail rotor gearbox chip Provisions for optional IIDS functions & Spares for optional equipment kits
ELECTRICAL Dual 28 volt dc system with 2 dc buses and 2 emergency buses One 17 ampere-hour nickel cadmium battery Two engine mounted 30 volt 200 ampere starter/ generators (derated to 170 ampere) Two solid state voltage regulators Ground fault detection system Interior lighting; cockpit utility light two cockpit dome lights two cabin dome lights White dimmable instrument lighting and utility light in cockpit Position lights External power receptacle Landing lights (2 fixed angle - high/low)
EMERGENCY, WARNING AND CAUTION INDICATORS • INSTRUMENT PANEL MOUNTED Engine Fire warning (2) Engine out warning (2) FADEC failure warning (2) (visual and audio) Rotor RPM caution (visual and audio) OEI Training Mode Selector Switch Main Gearbox Compartment Hot (Left&Right) Master Caution-direct attention to annunciation on IIDS indicating:
MISCELLANEOUS Keys for crew, passenger, and baggage compartment doors Manuals - flight, parts and maintenance Main and tail rotor tie downs Cargo tie downs loose Covers - engine air, oil cooler, exhaust and pitot Ground handling wheels, hydraulic
• IIDS WARNING, CAUTION, ADVISORY MESSAGES Battery overheating Battery hot Battery relay DC generator fail (2) Emergency bus pwr (2) Engine fuel pressure (2) Engine fuel filter (2) Engine fuel low (2) Engine fuel valve (opening) (2) Engine oil pressure, low (2) Engine oil temperature (2) External power door Engine sump chip (2)
Specifications subject to change without notice.
Product Specifications
11
427VFR January 2005
Optional Accessories BHT Factory Installed Kits • • • • •
REFER TO NOTES ON FOR KIT COMPATIBILITY
Part Number
Kit Description
• • • • •
Wt (lbs)
Wt (Kg)
Notes
AIRFRAME 427-706-010-103
HIGH SKID GEAR w/ Flitesteps
47.4
21.5 (1, 2
427-706-014-109
EMERGENCY FLOATATION EQUIPMENT w/Floatsteps
245.5
111.4 (1, 3
427-706-014-111
EMERGENCY FLOATATION PROVISIONS
3.2
1.5
427-706-014-105
BOTTLE GUARD
0.8
0.4 (4
427-706-016-101
CREW STEP LEFT for LOW & HIGH SKIDS
2.7
1.2
427-706-016-102
CREW STEP RIGHT for LOW & HIGH SKIDS
2.7
1.2
427-706-702-115
DUAL CONTROLS
15.7
7.1
AFT AUDIO ICS - 6 Station w/Headsets
15.3
6.9
AUDIO 427-705-002-101 AVIONICS 071-01523-0302
GPS DATABASE - AMERICAN
0.0
427-705-003-101
COMPASS SYSTEM KCS-55A PROV W/ KI-525A GYRO
427-705-003-103
COMPASS SYSTEM KCS-55A EQUIPMENT W/ KI-525A GYRO
8.9
4.0 (6
427-705-003-105
COMPASS SYS. KCS-55A PROV W/ KI-525A GPS CPL. TO KLN90B
1.4
0.6 (6, 7
427-705-003-107
COMPASS SYS. KCS-55A EQUP W/ KI-525A CPL. TO GPS KLN90B
9.0
4.1 (6, 7
427-705-004-101
TRANSPONDER PROVISION (KT-76C or KT-70)
0.8
0.4 (8
427-705-004-103
TRANSPONDER EQUIPMENT (KT-76C)
2.4
1.1 (8
427-705-004-105
TRANSPONDER EQUIPMENT (KT-70)
3.9
1.8 (8
427-705-006-101
OMNI W/ CDI KI203 INDICATOR
4.2
1.9
427-705-007-101
COMM #2 KY196A PROVISIONS
2.8
1.3
427-705-007-103
COMM #2 KY196A EQUIPMENT
2.8
1.3
427-705-009-101
GPS PROVISIONS (KLN-90B)
2.1
1.0
427-705-009-103
GPS EQUIPMENT (KLN-90B)
6.3
2.9 (5, 8, 9
427-705-010-101
ADF PROVISIONS (KR-87)
4.3
2.0
427-705-010-103
ADF EQUIPMENT (KR-87)
3.8
1.7
427-705-014-101
AVIONICS BLOWER
2.8
1.3 (9
427-705-015-101
NAV / COMM / AUDIO PANEL PROVISION KIT
8.0
3.6
427-705-015-103
NAV / COMM #1 EQUIPMENT ( KX-155A )
3.4
1.5 (9
427-705-015-105
NAV / COMM #1 EQUIPMENT ( KX-165A W / GLIDESLOPE )
3.4
1.5 (9
427-706-001-101
ENCODING ALTIMETER
0.9
0.4 (8
427-706-002-105
FLIGHT INSTRUMENTS
8.2
3.7 (6
427-706-003-101
ELT POINTER 4000
3.2
1.5
CREW VENTILATION PANEL OUTLETS
7.9
3.6
12.5
0.0 (5 5.7 (6, 7
ENVIRONMENT 427-706-009-101
Specifications subject to change without notice.
Product Specifications
12
427VFR January 2005
Optional Accessories (continued) BHT Factory Installed Kits • • • • •
REFER TO NOTES FOR KIT COMPATIBILITY
Part Number
• • • • •
Kit Description
Wt (lbs)
Wt (Kg)
Notes
EQUIPMENT
427-706-004-101
28 AMPS BATTERY
24.9
11.3 (1
427-706-706-103
ROTOR BRAKE
20.7
427-706-900-101
CARGO HOOK EQUIPMENT
31.4
427-706-900-103
CARGO HOOK PROVISIONS
3.1
1.4
427-705-500-103
SOUND-PROOFING, CORPORATE
7.4
3.4
427-705-502-109
INTERI OR TRIM, CORPORATE
10.8
4.9
427-705-504-105
CORPORATE HEADLINER KIT- 4 Lights
0.3
0.1
427-705-504-107
CORPORATE HEADLINER KIT- w/Air Conditioner - 4 Lights
5.1
2.3
427-705-506-101
CONSOLE AFT CABIN
12.0
5.4
427-705-506-103
CONSOLE FORWARD CABIN
12.0
5.4
427-705-702-101
4 PASS. CABIN CORPORATE CLUB SEATING
-6.9
-3.1
427-705-703-101
5 PASS. CABIN CORP. SEATING w/ 3 AFT FACING
-6.5
-2.9
427-705-703-103
5 PASS. CABIN CORP. SEATING w/ 2 AFT FACING
-0.5
-0.2
427-706-503-105
INTERNAL FLOOR FITTINGS, LH (CARGO TIE DOWNS)
7.2
3.3
427-706-503-106
INTERNAL FLOOR FITTINGS, RH (CARGO TIE DOWNS)
7.2
3.3
MARKINGS FOR HIGH VIS. M/R BLADES (WHITE & ORANGE)
0.0
0.0 (10
9.4 14.2 (4
INTERIOR
PAINT
HIGH VISIBILITY Credits EQUIPMENT
214-706-104-105
GROUND HANDLING WHEELS
95.0
43.1
Specifications subject to change without notice.
Product Specifications
13
427VFR January 2005
Optional Accessories (continued) Vendor STC Kits • • • • •
Part Number
REFER TO NOTES FOR KIT COMPATIBILITY
• • • • •
Kit Description
Wt (lbs)
Wt (Kg)
Notes
STC's AIRFRAME 427-510-002
DOOR HOLDER/OPENER (5 DOORS SET ,INCL. BAG. DOOR)
6.5
2.9
427-540-001
SLIDING WINDOW WITH LOCKS CREW L/H & R/H
1.0
0.5
427-600-001
SLIDING PASSENGER DOOR L/H
15.0
6.8
427-600-002
SLIDING PASSENGER DOOR R/H
15.0
6.8
ENVIRONMENT 427EC-200-1
AIR CONDITIONING STD LH EVAP.
101.4
46.0
427EC-200-2
AIR CONDITIONING OPT DUAL EVAP.
111.4
50.5
427EC-200-3
AIR CONDITIONING OPT RH EVAP.
101.4
46.0
427H-200-1
HEATER W/CHIN BUBBLE DEFROSTER 427H-988-1
20.5
9.3
9.0
4.1
EQUIPMENT 427-855-001
LANDING LIGHT, MOVABLE (NIGHTSCANNER)
427-995-001
RESCUE HOIST INCL. PROVISIONS
160.0
72.6
427-995-002
RESCUE HOIST INCL. PROV. ( FOR A/C W / EMER. FLTS. )
160.0
72.6
TBD
RESCUE HOIST PROVISIONS ONLY
TBD
TBD
965-37501-001
WIRE STRIKE - RECOMMENDED KIT - SEE NOTE Low Gear
15.8
7.2 (11
High Gear
16.3
7.4 (11
INTERIOR 427-451-001
FLOOR PROTECTOR (CREW )
1.4
0.6
427-452-001
FLOOR PROTECTOR (PASSENGER)
8.3
3.8
427-452-002
FLOOR PROTECTOR PAX FOR HEATER
7.6
3.4
427-453-001
FLOOR PROTECTOR (BAGGAGE)
6.5
2.9
Specifications subject to change without notice.
Product Specifications
14
427VFR January 2005
Optional Accessories (continued) Explanatory Notes • • • • •
REFER TO NOTES FOR KIT COMPATIBILITY
• • • • •
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 standard ship hardware removed. 2) Kit includes STC FlightSteps - steps (2) weigh 39.5 lbs (17.9kg). 3) Kit includes STC FloatSteps - steps (2) weigh 41.6 lbs (18.9kg). 4) Bottle Guard is required when Emergency Floats and Cargo Hook Equipment are both installed. 5) A GPS data base must be installed concurrently with the GPS Equipment (unit); Other geographic regions are available on request. 6) When a KCS-55A system is installed concurrently with the Flight Instruments, the Dir. Gyro. will be removed/credited by Sales Order (Kit Number is the same). 7) The GPS compatible KCS-55A requires BOTH the basic provisions kit AND the coupled provisions kit. 8) Encoding Altimeter or Blind Encoder (customizing) is required to enable Mode C/Mode S altitude reporting and/or GPS altitude input. Customer must obtain Aircraft ID code for Mode S. 9) The Avionics Blower Kit is required if not already installed. 10) Standard or High Visibility Main Rotor Blade Paint to be specified by Sales Order. 11) 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. STC Kits - Select Supplemental Type Certificated Optional Equipment Kits are available for i nstallation at the Bell Helicopter Textron factory. Please contact your Bell Sales Representative for availability and pricing information. P.O.R. - Priced On Request.
Specifications subject to change without notice.
Product Specifications
15
427VFR January 2005
INTENTIONALLY LEFT BLANK
Product Specifications
16
427VFR January 2005
IGE & OGE HOVER CEILINGS, OEI & TWIN SERVICE CEILINGS, PRATT & WHITNEY PW207D ENGINES PARTICLE SEPARATOR INSTALLED BLEED AIR OFF NOTES: 1) HOVER PERFORMANCE AND SERVICE CEILING CHARTS ARE BASED ON MINIMUM SPECIFICATION ENGINE POWER.
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
17
427VFR January 2005
IGE HOVER CEILING TWIN ENGINE OPERATION AT TAKEOFF POWER ZERO WIND OR HEADWIND PARTICLE SEPARATOR INSTALLED GROSS WEIGHT - 100 KG 23
24
25
26
27
28
29
10
30
3 0 ° C
MAX OAT LIMIT
28
9
26 8
24 OUTSIDE AIR TEMPERA TURE - °F
T F 0 0 0 1 E D U T I T L A E R U S S E R P
E D 12 U T 10 I T 0 L 0 8 A 0 1 E x 6 R T U F 4 S 2 S E R 0 P
7
6
5
0
20
40
60
80
100
120
MAX HP
B 0 L * 6 5 5 O A T N I M
T A O N I M
-30
3 M AX I M U M H D
-20
-10
2 M A X O A T
0
10
20
30
40
1 0
50
22
E D U T I T 0 L 0 A 0 1 E x R U M S S E R P
20 18 16
OUTSIDE AIR TEMPERA TURE - °C
14 * THE DASHED LINE REPRESENTS THE MINIMUM OAT LIMIT FOR INTERNAL GROSS WEIGHTS BETWEEN 6350 AND 6550 LB S
4
12 S B L 0 5 5 6
S B L 0 5 3 6
3
W G M U M I X A M E T A N R E T L A
W G L A N R E T N I M U M I X A M
2
1 SKID HEIGHT 4 FT (1.2 M)
10 8
S R E T E M 0 0 1 E D U T I T L A E R U S S E R P
6 4 2
0
0 50
52
54
56
58
60
62
64
66
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 LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
18
427VFR January 2005
OGE HOVER CEILING TWIN ENGINE OPERATION AT TAKEOFF POWER ZERO WIND OR HEADWIND PARTICLE SEPARATOR INSTALLED GROSS WEIGHT - 100 KG
23
24
25
26
27
28
29
10 3
0 ° M C A X O I S I I A S S A T A A + L I + + M 3 2 1 0 I 0 0 ° T ° C ( C ° C I S A + 3 6 . 7 ° C )
9
8
T F 0 0 0 1 E D U T I T L A E R U S S E R P
S B L 0 E 5 T 5 6 A N W R G E T M L U A M I X A M
- 2 0 ° - 1 C 0 ° C I S A
7 1
2 0 0 ° C ° C
M I N O A T L M - 1 I 0 I T
30 28 26 24 22 20
° C
6
0 ° C
18
- 2 0 ° C
16 5 14 40°C
4
12 10
3 8 L A N S R B E L T 0 N I 5 3 M 6 U M I W X G A M
2
1
0 50
52
54
56
58
60
62
64
S R E T E M 0 0 1 E D U T I T L A E R U S S E R P
6 4 2 0 66
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 LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
19
427VFR January 2005
OEI SERVICE CEILING OEI 30 MINUTE POWER PARTICLE SEPARATOR INSTALLED
GROSS WEIGHT - 100 KG
23
24
25
26
27
10
I S A + 2 0 ° 2 C 0 ° C
9
28
T F 0 0 0 1 E D U T I T L A E R U S S E R P
1 0 ° C
I S I S A A + 1 0 ° C
M A X O A T L I M I T ( I S A + 3 6 . 7 ° C )
7
S B L 0 E 5 T 5 6 A N W R G E T M M L A U I M N I X O A A T M L
- 2 0 ° C - 1 0 ° C
0 ° C
I S A + 3 0 ° C
8
29
I M I T
3 0 ° C
28 26 24 22 20
- 1 0 ° C
6
30
18 4 0 ° C
16
5 14 4
12 S B L 0 5 3 6
3
10 8
W G L A N R E T N I M U M I X A M
2
1
S R E T E M 0 0 1 E D U T I T L A E R U S S E R P
6 4 2
0
0 50
52
54
56
58
60
62
64
66
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 LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
20
427VFR January 2005
OEI SERVICE CEILING OEI CONTINUOUS POWER PARTICLE SEPARATOR INSTALLED
GROSS WEIGHT - 100 KG
23
24
25
26
27
28
10 I S A + 2 0 ° C
9 I S A + 3 0 ° C
1 0 ° C
M A X O A T L I M I T ( I S A + 3 6 . 7 ° C )
8
T F 0 0 0 1 E D U T I T L A E R U S S E R P
I S 0 A + 1 ° C 0 ° C
7
29 - 2 0 ° C - 1 0 ° C
S B L 0 E 5 T 5 6 A N W R G E T M M L U I N A M I O X A T A L M
I S A
I M I T
2 0 ° C
6
28 26 24 22 20
- 1 0 ° C
3 0 ° C
30
18 16
5 14
4 0 ° C
4
12 10
3 8 L A N S R B E L T 0 N I 5 3 M 6 U M I W X G A M
2
1
0 50
52
54
56
58
60
62
64
S R E T E M 0 0 1 E D U T I T L A E R U S S E R P
6 4 2 0 66
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 LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
21
427VFR January 2005
SERVICE CEILING TWIN ENGINE OPERATION AT MAXIMUM CONTINUOUS POWER PARTICLE SEPARATOR INSTALLED GROSS WEIGHT - 100 KG
23
24
25
26
27
28
29
10
30 MAX OAT LIMIT
28
9
26 OUTSIDE AIR TEMPERA TURE - °F
8
T F 0 0 0 1 E D U T I T L A E R U S S E R P
E D 12 U T 10 I T 0 L 0 8 A 0 1 E x 6 R T U F 4 S 2 S E R 0 P
7
6
0
20
40
60
80
100
MAXIMUM PRESSURE ALTITUDE
M A X I M U M O A T
B 0 L * 6 5 5 O A T N I M T A O N I M
-30
24
120
3 2 1 0
-20
-10
0
10
20
30
40
50
E D U T I T 0 L 0 A 0 E 1 x R U M S S E R P
22 20 18
OUTSIDE AIR TEMPERA TURE - °C
5
16
* THE DASHED LINE REPRESENTS THE MINIMUM OAT LIMIT FOR INTERNAL GROSS WEIGHTS BETWEEN 6350 AND 6550 LB S
14
4
12 S B L 0 5 5 6
S B L 0 5 3 6
3
W G M U M I X A M E T A N R E T L A
W G L A N R E T N I M U M I X A M
2
1
10 8
S R E T E M 0 0 1 E D U T I T L A E R U S S E R P
6 4 2
0
0 50
52
54
56
58
60
62
64
66
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 LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
22
427VFR January 2005
CATEGORY A PERFORMANCE PRELIMINARY DATA GROUND LEVEL OR ELEVATED HELIPAD DAY AND NIGHT PRATT & WHITNEY PW207D ENGINES PARTICLE SEPARATOR INSTALLED BLEED AIR OFF THE FOLLOWING CHARTS PRESENT CATEGORY A PROCEDURES & PERFORMANCE FOR NORMAL TWIN ENGINE AS WELL AS ONE ENGINE INOPERATIVE TAKEOFF & LANDING OPERATIONS. THE MODEL 427 IS NOT CERTIFIED UNDER FAR 29 SYSTEMS STANDARDS. THE M427 IS APPROVED FOR CATEGORY A HELIPAD TAKEOFF & LANDING PROCEDURES UP TO A MAXIMUM GROSS WEIGHT OF 6500 LBS (2948 KG) AND A MAXIMUM DENSITY ALTITUDE OF 4000 FEET, AS LIMITED BY THE APPLICABLE WAT LIMIT CHART. ADDITIONAL CHARTS FOR COMPLETED/REJECTED TAKEOFF DISTANCE, CLIMB DISTANCE [TO 200 & 1000 FEET], AND FOR CATEGORY A RUNWAY PROCEDURES WILL BE AVAILABLE IN THE SOON-TO-BE APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT. EQUIPMENT REQUIRED [INSTA LLED AND FUNCTIONAL] TO PERFORM CATEGORY A OPERATIONS: RADAR ALTIMETER
NOTE: GROUND LEVEL OR ELEVATED HELIPAD CATEGORY A OPERATIONS MAY BE ACCOMPLISHED BY ONE PILOT. INFORMATION ON THE FOLLOWING PAGES PROVIDES A BRIEF EXPLANATION OF CATEGORY A OPERATION CAPABILITY FOR THE BELL 427. THE WAT CHART INCLUDED MAY BE USED TO DETERMINE TAKEOFF OR LANDING WEIGHT CAPABILITY FOR BOTH GROUND LEVEL AND ELEVATED HELIPAD OPERATIONS. FOR SIMPLIFICATION, ONLY ILLUSTRATIONS DESCRIBING TAKEOFF ARE SHOWN.
DEFINITIONS: CATEGORY 'A' TAKEOFF;
OPERATION OF THE HELICOPTER IN SUCH A MANNER THAT IF ONE ENGINE FAILS AT ANY TIME AFTER THE START OF THE TAKEOFF THE HELICOPTER CAN: 1. PRIOR TO THE TDP (TAKEOFF DECISION POINT) RETURN TO AND SAFELY STOP ON THE TAKEOFF AREA; RT O (REJECTED TAKEOFF) ; OR 2. AT OR AFTER THE TDP , CLIMB OUT FROM THE POINT OF FAILURE AND ATTAIN SINGLE ENGINE FORWARD FLIGHT; CTO (CONTINUED TAKEOFF).
CATEGORY 'A' LANDING;
OPERATION OF THE HELICOPTER IN SUCH A MANNER THAT IF ONE ENGINE FAILS AT ANY TIME DURING THE LANDING APPROACH THE HELICOPTER CAN: 1. AT OR PRIOR TO THE LDP (LANDING DECISION POINT) CLIMB OUT FROM THE POINT OF FAILURE AND ATTAIN SINGLE ENGINE FORWARD FLIGHT; OR 2. AFTER THE LDP , SAFELY STOP ON THE LANDING AREA.
CATEGORY A PERFORMANCE & PROCEDURES SHOWN HERIN ARE PRELIMINARY - A CERTIFIED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT WILL BE PUBLISHED SOON
Product Specifications
23
427VFR January 2005
427 HELIPAD NORMAL TAKEOFF GROUND LEVEL OR ELEVATED HELIPAD NORMAL TAKEOFF PROFILE DAY AND NIGHT
THE HELIPAD NORMAL TAKEOFF TECHNIQUE CONSISTS OF A VERTICAL-REARWARD TAKEOFF TO THE CALCULATED TD P; THEN ACCELERATION TO V TOSS (45 KIAS), WITH SUBSEQUENT CLIMBOUT AT V Y (60 KIAS) AFTER PASSING 200FT.
[HELIPAD SIZE - 60 BY 60 FT 18.2 BY 18.2 M]
427 OEI HELIPAD TAKEOFF / REJECTED TAKEOFF GROUND LEVEL OR ELEVATED HELIPAD COMPLETED & REJECTED TAKEOFF PROFILE DAY AND NIGHT
THE HELIPAD OEI TAKEOFF TECHNIQUE CONSISTS OF A VERTICAL REARWARD TAKEOFF TO THE CALCULATED TDP; THEN ACCELERATION TO V TOSS (45 KIAS), WITH SUBSEQUENT CLIMBOUT AT V TOSS UP TO 1000 F T ABOVE TAKEOFF SURFACE. ENGINE FAILURE PRIOR TO THE CALCULATED TDP REQUIRES RETURN TO THE HELIPAD.
[HELIPAD SIZE - 60 BY 60 FT 18.2 BY 18.2 M]
CATEGORY A PERFORMANCE & PROCEDURES SHOWN HERIN ARE PRELIMINARY - A CERTIFIED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT WILL BE PUBLISHED SOON
Product Specifications
24
427VFR January 2005
HELIPAD TDP/LDP HEIGHT DETERMINATION CHART FOR A 15 FOOT MINIMUM GROUND CLEARANCE NOTE:
TO OBTAIN A MINIMUM GROUND CLEARA NCE HIGHER THAN 15 FT, INCREASE THE TDP / LDP HEIGHT OBTA INED FROM THIS CHART, BY THE ADDITIONAL GROUND CLEARA NCE REQUIRED.
HD = 4,000 FT
0 0 0 6
0 0 0 4
0 0 0 2
T A O
0
10
20
30
3 0 - 1 0
4 0 5 0
51. 7
- 2 0
L E V E L A E S 0 0 T 0 F 2 H P
N I M
-40 -30 -20 -10
1 0 2 0 0 &
M A X O A T
- ° C O A T - 3 0
40
50
60 180
OAT - °C
160
T I G H E W S S G R O
140
TDP / LDP HEIGHT ABOVE THE TAKEOFF SURFACE FT
0 6 2 0
120
0 6 0 0
100
0 5 8 0
80
0 5 6 0
60
0 5 4 0
40
0 5 2 0
20
USING THE CHART;
L B S
0 6 5 0 0 6 4 0
MINIMUM TDP / LDP HEIGHT IS 25 FT ABOVE THE TAK EOFF SURFACE
5000 OR LESS
1. ENTER THE CHART AT THE APPROPRIATE OA T (OUTSIDE AIR TEMPERATURE) AND MOVE UP VERTICALLY TO THE PRESSURE ALTITUDE (H P ) LINE CORRESPONDING TO THE HELIPAD. 2. MOVE RIGHT HORIZONTALLY TO THE APPROPRIATE OAT LINE. 3. MOVE DOWN VERTICALLY TO THE APPROPRIATE GROSS WEIGHT LINE. 4. MOVE LEFT HORIZONTALLY AND READ THE TAKEOFF / LANDING DECISION POINT HEIGHT WITH ZERO HEADWIND.
NOTE: CATEGORY A HELIPAD TAKEOFF AND LANDING HAS NOT BEEN DEMONSTRATED AND IS NOT APPROVED ABOVE 4,000 FEET / 1219 METERS DENSITY ALTITUDE . CATEGORY A PERFORMANCE & PROCEDURES SHOWN HERIN ARE PRELIMINARY - A CERTIFIED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT WILL BE PUBLISHED SOON
Product Specifications
25
427VFR January 2005
CATEGORY A TAKEOFF AND LANDING WAT LIMIT GROUND LEVEL AND ELEVATED HELIPAD (DAY AND NIGHT) PRATT & WHITNEY PW207D ENGINE PARTICLE SEPARATOR INSTALLED GROSS WEIGHT - KGS 2300
2400
2500
2600
2700
2800
2900
7000
S B L 0 5 3 6 = W G
6000
T F E D U T I T L A E R U S S E R P
CATEGORY A HELIPAD PROFILE TAKEOFF & LANDING DENSITY AL TITUDE LIMIT IS 4000 FT HD
5000
S B L 0 0 5 6 = W G M U M I X A M
4000
2000 1800 1600 1400 1200 1000
3000 800 2000
600 400
1000
0
200
0 2 -
C ° T A O
S R E T E M E D U T I T L A E R U S S E R P
0
0 3 -
0 1 -
-200
-1000 5100
5300
5500
5700
5900
6100
6300
6500
GROSS WEIGHT - LBS
USING THE CHART;
1. ENTER THE CHART AT THE PRESSURE ALTITUDE OF THE TAKEOFF / LANDING HELIPAD. 2. MOVE RIGHT HORIZONTALLY TO THE APPROPRIATE OA T (OUTSIDE AIR TEMPERATURE) LINE OR TO THE MAX GROSS WEIGHT LINE (WHICHEVER IS LESS). 3. MOVE DOWN VERTICALLY AND READ THE TAKEOFF & LANDING CAPABILITY GROSS WEIGHT.
CATEGORY A PERFORMANCE & PROCEDURES SHOWN HERIN ARE PRELIMINARY - A CERTIFIED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT WILL BE PUBLISHED SOON
Product Specifications
26
427VFR January 2005
FUEL FLOW vs AIRSPEED ISA & ISA+20 °C PRATT & WHITNEY PW207D ENGINES PARTICLE SEPARATOR INSTALLED BLEED AIR OFF NOTES: 1) THE BEST ALLOWABLE CRUISE SPEED IS EITHER LONG RANGE CRUISE [LRC] SPEED , OR WHEN SPEED IS LIMITED BY MAXIMUM CONTINUOUS POWER [MCP] OR Vne , THE MAXIMUM SPEED PERMITTED. 2) FUEL FLOW vs AIRSPEED CHARTS ARE BASED ON AVERAGE NEW ENGINE POWER. FOR MINIMUM SPECIFICATION ENGINE FUEL FLOW ADD 3%.
Product Specifications
27
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = SEA LEVEL OAT = +15 °C PARTICLE SEPARATOR INSTALLED
80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 100 95
520
TRANSMISSION LIMIT
230
500 LRC
220
90
480
85
460
210
440
200
80 75 70 % E65 U Q R60 O T 55 50 45
420 R H / B400 L W380 O L F L360 E U F 340
L B 0 0 - 1 5 . G W 6 5 6 0 5 5
320
40 35 30
190 R H / G 180 K W 170 O L F L 160 E U F
300
3 6
4 0
5 0 4 5
150
VNE
140 130
280
MAX ENDURANCE
25
120
260 240
110
220
100 40
40
50
50
60
60
70
80 90 100 110 120 TRUE AIRSPEED - KNOTS
130
70 80 90 100 110 120 130 INDICATED AIRSPEED - KNOTS
140
140
150
160
150
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
28
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 2000 FT OAT = + 11 °C PARTICLE SEPARATOR INSTALLED 80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520 100 95
230
TRANSMISSION LIMIT
500
220
480 LRC
90 460
210
440
200
85 80 75 70 % E65 U Q R60 O T 55 50 45
R420 H / B400 L W380 O L F L360 E U F 340
40 35
280
30 25
L B 0 0 - 1 W 5 . G 6 5 6 0
5 5
320 300
190 R H / G 180 K W 170 O L F L 160 E U F
4 0
150
VNE
5 0 4 5
140
3 6
130 120
MAX
260
ENDURANCE
240
110
220
100 40
50
40
60
50
70
60
80 90 100 110 120 TRUE AIRSPEED - KNOTS
130
70 80 90 100 110 120 INDICATED AIRSPEED - KNOTS
140
130
150
140
160
150
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
29
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 4000 FT OAT = + 7 °C PARTICLE SEPARATOR INSTALLED 80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520 230
500
TRANSMISSION LIMIT
100 95 90
460
85
440
80 75 70 % E65 U Q R60 O T 55 50 45
220
480
210 LRC
200
420 R H / B400 L W380 O L F L360 E U F 340
B L 0 0 1 5 W . G 5 6 6 0
140
5 0
300 280
35
25
150
VNE
5 5
320
40
30
190 R H / G 180 K W 170 O L F L 160 E U F
3 6
260
4 0
4 5
130 120
MAX
240
110
ENDURANCE
100
220 40
50
40
60
50
70
60
80 90 100 110 120 TRUE AIRSPEED - KNOTS
130
140
150
70 80 90 100 110 120 INDICATED AIRSPEED - KNOTS
130
140
160
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
30
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 6000 FT OAT = + 3 °C PARTICLE SEPARATOR INSTALLED 80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520 230
500 100 95
220
TRANSMISSION LIMIT
480 460
210
440
200
90 85 80 75 70 % E65 U Q R60 O T 55
LRC
R420 H / B400 L W380 O L F L360 E U F 340
5 . 6 5
MAX ENDURANCE
320
5 5 5 0
300
40
280
35
260
30
240
25
4 0 3 6
150
6 0
50 45
190 R H / G 180 K W 170 O L F L 160 E U F
VNE
140 130
4 5
G W
B 0 L 0 - 1
120 110 100
220 40
50
40
60
50
70
80 90 100 110 120 TRUE AIRSPEED - KNOTS
60 70 80 90 100 110 INDICATED AIRSPEED - KNOTS
130
120
140
150
130
160
140
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
31
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 8000 FT OAT = - 1 °C PARTICLE SEPARATOR INSTALLED 80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520 230
500 100
220
480
TRANSMISSION LIMIT
95
460
210
90
440
200
85
R420 H / B400 L W380 O L F L360 E U F 340
80 75 70 % E65 U Q R60 O T 55 50 45 40
LRC
5 . 5 6 MAX
320
150
6 0
ENDURANCE
5 5
300
140
5 0
280
4 5
260
130 VNE
120
4 0
35
3 6
240 30 25
190 R H / G 180 K W 170 O L F L 160 E U F
L B 0 0 - 1 G W
110 100
220 40
50
60
40
50
70
80 90 100 110 120 TRUE AIRSPEED - KNOTS
130
60 70 80 90 100 110 INDICATED AIRSPEED - KNOTS
140
120
150
130
160
140
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
32
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = SEA LEVEL OAT = + 35 °C PARTICLE SEPARATOR INSTALLED
80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 100 95 90
240
TRANSMISSION LIMIT
520
230
500
LRC
220
480
85 80 75 70 % E65 U Q R60 O T 55 50
460
210
440
200
420 R H / B400 L W380 O L F L360 E U F 340
L B 0 0 - 1 5 G W . 6 5 6 0 5 5
45 40
320
35
300
30
280
190 R H / G 180 K W 170 O L F L 160 E U F
3 6
4 0
5 0 4 5
150
VNE
140 130
MAX ENDURANCE
25
120
260 240
110
220
100 40
50
40
60
50
70
60
80 90 100 110 120 TRUE AIRSPEED - KNOTS
130
70 80 90 100 110 120 INDICATED AIRSPEED - KNOTS
140
130
150
140
160
150
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
33
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 2000 FT OAT = + 31°C PARTICLE SEPARATOR INSTALLED
80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520
100
TRANSMISSION LIMIT
230
500
95
LRC
220
90
480
85
460
210
80
440
200
75 70 % E65 U Q R60 O T 55 50
R420 H / B400 L W380 O L F L360 E U F 340
45 40 35
B L 0 0 1 5 W . G 6 5 6 0
5 5
320 300 3 6
280
30 25
190 R H / G 180 K W 170 O L F L 160 E U F
4 0
150
VNE
5 0 4 5
140 130
MAX
260
120
ENDURANCE
240
110
220
100 40
50
40
60
50
70
60
80 90 100 110 120 TRUE AIRSPEED - KNOTS
130
140
150
70 80 90 100 110 120 INDICATED AIRSPEED - KNOTS
130
140
160
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
34
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 4000 FT OAT = + 27 °C PARTICLE SEPARATOR INSTALLED 80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520 100 95
230
TRANSMISSION LIMIT
500
MIN SPEC ENGINE - MCP
220
480
90
210
460 85 80 75 70 % E65 U Q R60 O T 55
LRC
R420 H / B400 L W380 O L F L360 E U F 340
40
6 0
300 280
30
260
150
5 5
320
35
190 R H / G 180 K W 170 O L F L 160 E U F
L B 0 0 - 1 5 G W 6 5.
50 45
200
440
3 6
4 0
5 0 4 5
VNE
140 130 120
MAX
25
110
ENDURANCE
240
100
220 40
50
40
60
50
70
80 90 100 110 120 TRUE AIRSPEED - KNOTS
60 70 80 90 100 110 INDICATED AIRSPEED - KNOTS
130
140
120
150
130
160
140
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
35
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 6000 FT OAT = + 23 °C PARTICLE SEPARATOR INSTALLED
80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520 100
500
95
480
90 85 80 75 70 % E65 U Q R60 O T 55 50 45 40
230 TRANSMISSION LIMIT MIN SPEC + 4 PERCENT ENGINE MIN SPEC ENGINE - MCP
460
210
440
200
420 R H / B400 L W380 O L F L360 E U F 340
190 R H / G 180 K W 170 O L F L 160 E U F
LRC
L B 0 0 - 1 W G 5 . 6 5 6 0
320
150
5 5
300
5 0 4 5
280
35 260
3 6
30 25
220
240
140 VNE
130
4 0
120 110
MAX ENDURANCE
100
220 40
50
60
40
50
70
80 90 100 110 120 TRUE AIRSPEED - KNOTS
130
60 70 80 90 100 110 INDICATED AIRSPEED - KNOTS
140
120
150
160
130
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
36
427VFR January 2005
FUEL FLOW
VS AIRSPEED
PRESSURE ALTITUDE = 8000 FT OAT = + 19 °C PARTICLE SEPARATOR INSTALLED 80
100
TRUE AIRSPEED - KM/HR 140 160 180 200 220
120
240
260
280
540 240 520 100 95
460
85
440
80
R420 H / B400 L W380 O L F L360 E U F 340
70 % E65 U Q R60 O T 55 50 45
TRANSMISSION LIMIT
480
90
75
230
500
220
MIN SPEC + 8 PERCENT ENGINE MIN SPEC + 4 PERCENT ENGINE
210
MIN SPEC ENGINE - MCP
200
LRC
5 . 5 6
MAX ENDURANCE
6 0
150
5 5
140
320 300
40
280
35
260
30
240
25
220
190 R H / G 180 K W 170 O L F L 160 E U F
5 0 4 5
130 VNE
120
4 0 3 6
40
50
40
60
50
70
B 0 L 0 - 1 G W
80 90 100 110 120 TRUE AIRSPEED - KNOTS
110 100 130
60 70 80 90 100 110 INDICATED AIRSPEED - KNOTS
140
120
150
160
130
THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATION S FOR ANY SPECIFI C FLIGHT MISSION, REFERENCE MU ST BE MADE TO THE APPR OVED FLIGHT MANUAL.
Product Specifications
37
427VFR 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; subpolar, 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 t hese 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
38
427VFR January 2005
COST OF OPERATIONS (co ntinued) 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
39
427VFR January 2005
SAMPLE - DIRECT COST OF OPERATIONS US DOLLARS PER FLIGHT HOUR OPERATOR OVERHAUL Fuel, Lubricants Fuel: (Note 1) [69 gallons per hour] Lubricants: 3% of Fuel Cost
$155.25 4.66
Airframe Direct Maintenance Labor: (Note 2) Inspection Overhaul Unscheduled and On-Condition
(0.366 MH/FH) (0.102 MH/FH) (0.744 MH/FH)
Parts: Inspection Retirement Overhaul Unscheduled and On-Condition
23.76 6.64 48.35
3.24 101.69 35.12 76.70
Powerplant Direct Maintenance Engine Overhaul (Including Accessories- Note 3 ) Line Maintenance (Labor) (0.119 MH/FH) Total Average Cost Per Hour(Note 4)
131.50 7.75 $594.66
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. Note 4: Increased Gross Weight Kit adds approximately $5.10 per Flight Hour.
M/R Hub Assy Mast Assembly Transmission
Product Specifications
COMPONENT OVERHAUL INTERVALS (Hours) 2,500 Swashplate Assembly 2,500 Starter Generator 3,000 T/R Gearbox 1,800 Rotor Brake Caliper 3,000 T/R Hub Assembly 2,500 Fanshaft Hgr. Assy.
40
1,000 5,000 3,000
427VFR January 2005
LIMITED LIFE COMPONENTS PART NUMBER
LIFE IN FLIGHT HOURS
COMPONENT
MAIN ROTOR HUB AND BLADE 406-010-108-135 Grip 406-010-115-131 Upper Plate Assembly 406-010-117-129 Lower Plate Assembly 406-010-120-105 Main Rotor Blade Bolt 407-010-103-115 Pitch Horn 427-010-103-105 Lower Cone Seat 427-010-105-107 Drive Ring Set MAIN ROTOR CONTROLS 406-010-413-141 Pitch Link Tube SWASHPLATE DRIVE ASSEMBLY 206-010-408-103 Lever Pin 406-010-407-101 Collective Idler Link 406-010-410-125 Inner Ring 406-010-411-117 Outer Ring 406-010-417-109 Bearing & Liner Assembly 406-010-419-117 Cap Assembly 406-010-432-101 Anti-Drive Link Assembly 427-010-403-101 Swashplate Pivot Sleeve Assembly 427-010-405-101 Swashplate Support Assembly 427-010-407-101 Collective Lever 427-010-408-101 Drive Lever 427-010-410-101 Drive Link 427-010-418-105 Anti-Drive Lever Assembly BOOSTED FIXED CONTROLS 407-001-022-149 Collective Tube - Lower 407-001-025-125 Collective Tube - Upper 427-001-502-101 Actuator Support 427-001-512-101 Collective Bellcrank Support 427-001-522-101 Collective Transmission Bellcrank 427-001-535-101 Idler Link TAIL ROTOR AND CONTROLS 406-012-102-109 T/R Yoke 427-016-001-109 T/R Blade DRIVE SYSTEM 206-340-300-105 Input Driveshaft 427-040-040-101 Main Rotor Mast PYLON SUPPORT STRUCTURE 427-010-201-107 L/H Pylon Side Beam 427-010-201-108 R/H Pylon Side Beam 427-010-204-101 Pitch Restraint Spring 427-010-207-101 Stop Fitting Assy - Left 427-010-209-101 Stop Fitting Assy - Right FIRE PROTECTION SYSTEM Cartridge Fire Ext. (J1 PORT - 10 YRS) 30600-12 Cartridge Fire Ext. (J2 PORT - 10 YRS) 30600-13
QTY PER A/C
LIST PRICE (EA)
1,500 2,500 2,500 10,000 2,500 5,000 5,000
4 1 1 8 4 1 1
$7,364.00 $6,739.00 $6,138.00 $1,971.00 $4,138.00 $23,763.00 $9,701.00
$19.64 $2.70 $2.46 $1.58 $6.62 $4.75 $1.94
5,000
4
$5,553.00
$4.44
5,000 5,000 5,000 5,000 5,000 2,500 5,000 10,000 10,000 10,000 5,000 5,000 10,000
1 1 1 1 1 1 1 1 1 1 2 2 1
$184.00 $729.00 $8,846.00 $12,760.00 $1,099.00 $1,976.00 $2,848.00 $8,031.00 $11,153.00 $5,796.00 $1,487.00 $1,776.00 $8,667.00
$0.04 $0.15 $1.77 $2.55 $0.22 $0.79 $0.57 $0.80 $1.12 $0.58 $0.59 $0.71 $0.87
10,000 10,000 5,000 10,000 10,000 5,000
1 1 1 1 1 1
$1,430.00 $1,887.00 $18,251.00 $1,311.00 $532.00 $3,121.00
$0.14 $0.19 $3.65 $0.13 $0.05 $0.62
5,000 5,000
1 2
$9,153.00 $21,954.00
$1.83 $8.78
5,000 5,000
2 1
$30,751.00 $28,689.00
$12.30 $5.74
2,500 2,500 10,000 2,500 1,500
1 1 1 1 1
$10,174.00 $10,478.00 $6,631.00 $4,058.00 $3,650.00
$4.07 $4.19 $0.66 $1.62 $2.43
10,000 10,000
2 2
$1,012.00 $966.00
$0.20 $0.19
Prices and hours are subject to change without notice.
TOTAL
TOTAL COST (FLT HR)
$101.69
THESE DATA ARE PROVIDED FOR ILLUSTRATION PURPOSES. CONSULT MAINTENANCE DOCUMENTS AND BHT SPARE PARTS PRICING FOR CURRENT, OFFICIAL INFORMATION.
Product Specifications
41
427VFR January 2005
PAINT SELECTION NOTES: 1. COLOR RENDERINGS (ORIGINAL) MUST BE PROVIDED F OR 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
42
427VFR January 2005
CUSTOMER SERIAL NO. REGISTRATION NO.
Standard Scheme A #427-1/01-A
BASE COLOR
ACCENT COLOR
MAJOR COLOR
NAME
NAME
NAME
NUMBER
NUMBER
NUMBER
Standard Scheme B #427-1/01-B
BASE COLOR
ACCENT COLOR
MAJOR COLOR
NAME
NAME
NAME
NUMBER
NUMBER
NUMBER
BASE COLOR
ACCENT COLOR
MAJOR COLOR
NAME
NAME
NAME
NUMBER
NUMBER
NUMBER
Standard Scheme C #427-1/01-C
R O L O C R O J A M
R O L O C T N E C C A
e m e h c S m o t s u C
R E M O T S U C
. O N L A I R E S
. O N N O I T A R T S I G E R
R O L O C E S A B
E M A N
R E B M U N
E M A N
R E B M U N
E M A N
R E B M U N
STANDARD PAINT SCHEMES COLOR SELECTION SAMPLES
A 427-5/99-A
B 427-5/99-B
C 427-5/99-C