BELL HELICOPTER BELL 430 Product Data Download Page 49 | Manualshive

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THIS IS AN UNCONTROLLED DOCUMENT.

THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED.

THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE

FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE.

PRODUCT DATA

JANUARY 2003

The Integrated Instrument Display System (llDS) consists of a single integrated color
active matrix liquid crystal display (LCD) unit to display and process the airframe
and engine instrumentation information accurately, and provide caution, warning and
advisory annunciation and controls. The IIDS also performs engine parameter exceedance
monitoring and records these exceedances and faults in nonvolatile memory (NVM)
for maintenance purposes. Warm-up time for the IIDS does not exceed five minutes
after a cold non-operational period at -45°C for ten hours. The IIDS power consumption
does not exceed 120 watts at maximum display brightness not taking into account display
heaters. The displayed data and symbology is crisp and clear and does not have any
smearing effect which would reduce information legibility. The display is consistent
and parameter recognition is easy. Digit and label size is distinct and easy to read to
minimize pilot or crew effort to extract information. The IIDS display is fully readable
under all ambient display illumination as low as 100 ft-lamberts. The display has a
contrast ratio of 10:1 minimum under all possible lighting conditions (day or night) within
viewing angles of 45° ± 5° vertical axis and ±45° horizontal axis. IIDS display colors
are consistent with other flight compartment equipment displays. The colors are white,
red, green, cyan and yellow. Alphanumerics are sized in order to ensure good readability
from both the pilot and copilot positions.

INTEGRATED INSTRUMENT DISPLAY SYSTEM [ IIDS ]

CENTER SECTION

115

89

115

726 649

91

12

99

99

60

63

302

28 2

76

28

27

07

9

9

5

4

ALT

ALT

ECU

OVSPD

OVSPD

103

ENG FIRE

1 FLTR

AUTOTRIM

EXT PWR

800

920

1 E/OIL

XMSN CHP

ENG2 C/FL

OPEN

NOTE: DETAILED SYSTEM INFORMATION

FOR THE ROGERSON KRATOS IIDS MAY

BE FOUND IN THE ATTACHED DOCUMENT;

LINK (RK-IIDS-PHB10-97.PDF)

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Summary of Contents for BELL 430

Page 1: ...Product Data ...

Page 2: ...of Bell Helicopters to prospective customers This data includes proprietary material of BHTI Disclosure reproduction or use of any of the material herein by persons other than BHTI employees and BHTI Independent Representatives International Dealers is forbidden without written permission from BHTI The PHOTOGRAPHS and DRAWINGS appearing herein are for illustration only and may differ from the actu...

Page 3: ... AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 BELL 430 PRODUCT DATA CONTENTS SECTION ONE GENERAL DESCRIPTION OF THE STANDARD CONFIGURATION SECTION TWO OPTIONAL EQUIPMENT FACTORY INSTALLED BHTC VENDOR STC KITS SECTION THREE DIMENSIONS DESIGN SPECIFICATIONS AND WEIGHTS ALPHABETICAL INDEX ...

Page 4: ...our equals 0 54 knots or 0 62 statute miles per hour Knots Nautical miles per hour Meter meters One meter equals 3 28 feet Statute miles per hour One mile per hour equals 0 87 knots Nautical miles Statute miles Kilogram kilograms Pound pounds One pound equals 0 45 kilograms In ground effect Hovering near the ground creates a cushion of air that increases the weight carrying capability of the helic...

Page 5: ...THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 SECTION ONE GENERAL DESCRIPTION OF THE STANDARD CONFIGURATION ...

Page 6: ...IS IS AN UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ...

Page 7: ...The Bell 430 FOUR BLADED bearingless rotor system features primary structural elements constructed of composite materials to avoid corrosion and to provide benign easily detectable failure modes along with on condition no retirement life operation Main rotor blade pitch change as well as flapping and lead lag motions occur through flexing and bending the two composite yokes with fluid filled dampe...

Page 8: ...TER DOOR OPTIONAL LITTER DOOR BAGGAGE DOOR MAIN PASSENGER DOOR COMFORT FEATURES The spacious cabin is easily entered through the wide nearly 180 opening passenger doors and provides comfortable seating for seven standard seats with ample room for baggage The 1 05 cubic meter 37 2 cubic feet aft baggage compartment is accessible through it s own door or through the rear cabin partition Cabin furnis...

Page 9: ...n drop tested when 75 full from 15 meters 50 feet without spillage and are interconnected with break away self sealing fittings The engines selected for the Bell 430 are the Rolls Royce 250 C40B These are a growth version of the well proven 250 C30 engine series from Rolls Royce which provide reliable power under the extremes of climatic conditions The Rolls Royce 250 engine series has accumulated...

Page 10: ...e IIDS is a valuable tool which also helps to increase the helicopter s reliability and maintainability INTEGRATED INSTRUMENT DISPLAY SYSTEM IIDS SHOWN WITH OPTIONAL EQUIPMENT MAINTAINABILITY FEATURES The Bell 430 is engineered for reliability and ease of maintenance Built in steps and work platforms along with plentiful access panels doors and inspection windows provide for quick and thorough pre...

Page 11: ...MATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 The basic airframe of the Bell 430 is provided with complete provisions for delivery in either of two configurations the standard SKID LANDING GEAR or the optional RETRACTABLE TRICYCLE WHEEL LANDING GEAR LANDING GEAR CHOICE ...

Page 12: ...ometers North of Montreal The plant is a short drive from Dorval International Airport The 152 acre site in Mirabel includes a 529 000 square foot facility that houses manufacturing fabricating processing assembly engineering design research and development product support engineering marketing and administration The Bell 430 is certified under FAR Part 29 Category B requirements Additionally the ...

Page 13: ...kling Polyurethane paint Not only is it durable and easy to keep clean but it maintains and in fact exemplifies the high standard of Bell quality and dependability The standard Bell 430 comes in THREE basic color scheme designs illustrated below each in THREE colors The colors are selected from the many shown in the IMRON paint chip chart available from the Bell representative A Special company co...

Page 14: ...orporates all of the redundant systems necessary for Category A certification The pilot must occupy the right front seat A passenger seat is provided on the left which may also carry a copilot with the addition of the optional dual flight control kit provisions for this kit are standard Seven additional passengers can be accommodated in the spacious main cabin Passengers can enter the cabin from e...

Page 15: ...ness and inertia reel with Quick Release mechanism 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 Each crew and passenger seat is equipped with a restraint assembly that consists of an inertia reel a shoulder harness pilot left front seat have double straps the passenger cabin has single straps ...

Page 16: ...ion weight All leather or vinyl is available as an option This configurations also available with optionalenergy attenuating either with or withoutfolding seatbacks passenger seats CABIN SEATING INTERIOR CHOICES Corporate Interior This optionalhigher level of interior trim complements the executive seating but may also be specified with the standard seating and includes Floor covered with tightly ...

Page 17: ...B arrangement with one row of three facing rearward and one row of three facing forward Available in eight color coordinated choices of fabric covered cushions 88 0 lbs 39 9 Kg when installed a net decrease of 3 7 lbs 1 7 Kg All leather is available as an option Additional Corporate Seating Arrangements Cabin seating options with four or five passenger seats in the cabin and one or two refreshment...

Page 18: ...d energy attenuating seats with individual seat belts and single strap shoulder harness and inertia reel arranged with one row of two and two rows of three forward facing seats The outboard two seats in the middle row fold forward to provide access to the rear row Available in DARK RED BLUE BROWN or GRAY fabric covered cushions 134 0 lbs 60 8 Kg when installed a net increase of 48 3 lbs 21 9 Kg Al...

Page 19: ... a broad range of Hospital Based or Public Agency medical transport and critical care requirements The Bell 430 cabin offers ample space for either single or dual pivoting litter installations The 158 cubic foot 4 5 M3 cabin volume provides an unmatched work area for multiple medical attendants with care provided at the head of the patient along with a complete complement of fixed and portable lif...

Page 20: ... BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 When cargo is transported it may be secured against shifting by attachment of straps and tie down rings to the 16 recessed studs found in the cabin floor The studs are all stressed for maximum loads of 1134 kilograms 2500 pounds force from perpendicular to 30 in any direction CARGO ...

Page 21: ...ty blanket which fits between the headliner and interior trim panels and the airframe The blanket is constructed from alternating layers of sound attenuating composite foam lead foil and vinyl covered fiberglass batting Access panels and bulkhead passages for wiring ducting and plumbing are sealed to eliminate extraneous sound paths The installation iscompatible withonly the STANDARD INTERIOR TRIM...

Page 22: ... metal strap with a strong spring action is mounted on the bottom edge of the door to hold it in the open position The external door handles are flush mounted spring loaded levers which are easy to grasp and turn The internal handles are of the lift up type with an adjacent hinged assist handle A common keyed lock is shared with the cabin baggage doors DOCUMENT STOWAGE Provisions for stowage of do...

Page 23: ...se and roof Each crew door window has a clear vision window in it s upper center section The small window is hinged at the bottom latched at it s top and is sealed for protection against wind and water A windshield wiper is installed on each windshield The wipers operate in synchronization and are controlled by a single switch located on the overhead console The switch has four positions HIGH LOW ...

Page 24: ...e clips at the ends of the shoulder harness straps One release motion serves to disengage the buckle and straps The inertia reel locks automatically to restrain the seat occupant when it senses sudden deceleration Each of the crew seats weighs approximately 12 7 kilograms 28 pounds CREW SEATING FEATURES The seat back is supported by three vertical columns which permit up and down adjustment of up ...

Page 25: ...ruments with ample space to add a wide selection of options Visibility forward and to the side is excellent due to the panel s low compact design The standard VHF AM communications system VHF comm No 1 is a King KTR 908 lightweight airborne radio It provides two way amplitude modulated voice communications within the frequency range of 118 000 MHz to 135 975 MHz The radio s control head is located...

Page 26: ...n a quick release bracket it is readily accessible to the pilot or passengers A first aid kit is mounted in between the two cockpit seats COCKPIT FURNISHINGS Two ash trays one on each side of the cockpit are located near the forward door posts at arm level An aircraft DC electric powered cockpit utility light is located at the rear of the overhead control panel It may be removed from its mounting ...

Page 27: ...approach plate holder and directable map light are located on the pilots door The approach plate holder swings up into position near the standby magnetic compass directly below the map light A convex safety mirror on the left inside door post allows the pilot to observe cabin security loading passengers at a glance with a minimum of effort and upper body movement SAFETY MIRROR APPROACH PLATE HOLDE...

Page 28: ... at their forward edge and swing open through nearly 180 to present an almost unobstructed threshold to the cabin The door opening is 0 9 meters 35 6 inches wide by 1 45 meters 57 inches high The three point latching system and slam closing feature insure a secure tight fit when closed The flush exterior handles common keyed lock and full perimeter sealing are the same as for the crew doors Additi...

Page 29: ...eters 1 7 feet high and serve as emergency exits when pushed out at the lower corners EMERGENCY EXITS CABIN FURNISHINGS Included in the standard interior trim are entry assist straps at each cabin door hinged door closure assist handles four ash trays durable padded VINYL floor covering or plush NYLON loop carpet hat rack stowage area and cabin dome lights Six ash trays are located in the outboard...

Page 30: ...ks and individual lap belts shoulder harnesses meet the latest FAR specifications for occupant restraint The seats are comfortably upholstered in flame retardant fabric and feature advanced ergonomic design The seats are secured to the floor of the cabin with quick release positive locking ring on stud type fasteners They are easily removed in only moments to convert the cabin for carriage of larg...

Page 31: ...4 8 inches 88 4 centimeters between the front and middle rows 35 6 inches 91 2 centimeters between the middle and aft rows These seat pitch values are well in excess of the 30 to 32 inches found in the coach section of jet airliners The standard left and right cabin doors open to an unobstructed area of 3 feet 92 centimeters wide by 4 feet 122 centimeters high An optional hinged panel door kit is ...

Page 32: ... from moving the pilot s flight controls Conventional helicopter flight controls are provided to control attitude altitude and direction Inputs from the cyclic and collective controls are transmitted to the MAIN ROTOR and inputs to the anti torque directional control pedals are transmitted to the TAIL ROTOR The flight control system is a direct mechanical linkage using only push pull tubes and bel...

Page 33: ...smitter Space is provided on the grip for additional switches used to control optional equipment A friction adjustment control located at the cyclic s base allows the pilot to set the desired amount of control resistance CYCLIC STICK GRIP The cyclic control stick attaches to the floor directly in front of the pilot s seat A direct linkage beneath the floor separates fore and aft and lateral inputs...

Page 34: ... This insures correct identification of engine throttle The Bell 430 collective lever incorporates some unique design features which reduce pilot effort and enhance safe operation The collective operates in a near horizontal arc i e increasing collective pitch equates to more rearward than upward motion of the lever perpendicular to any vertical rotor system vibrations which eliminates any pilot i...

Page 35: ... of both engines simultaneously when moved fore aft for fine adjustment of rotor RPM A collective control box is attached just below the throttles It contains the FADEC MATCHING switch which selects either torque or temperature matching for the engines the idle stop release switch which permits the respective throttles to advance past idle or to be closed the landing searchlight s on off stow and ...

Page 36: ... allows approximately 10 2 centimeters 4 inches fore aftmovement of the pedals relative to the pilots feet Provisions exist for both the addition of the optional dual copilot control kit and the hydraulic brake pedals of the optional wheel landing gear This system transmits movement from the control pedals to the tail rotor The direct linkage under the floor transmits input through the belly contr...

Page 37: ... collective control system are operated by both systems which are designated PC 1 and PC 2 Additionally the directional control ANTI TORQUE system servo actuator is powered by PC 1 and provisionsexist for PC 2 to power the optional wheel landing gear retraction mechanism Both systems operate continuously but may beindividually de energized for functional preflight system check Two switches HYD 1 H...

Page 38: ...ed a bypass valve opens Each module incorporates two relief valves which eliminate residual or thermal induced pressure from the systems after shutdown The pumps and reservoirs are coupled to the integrated modules by flexible hoses with quick disconnect fittings which allow a standard hydraulic ground power unit hydraulic mule to be attached for system maintenance checks HYDRAULIC RESERVOIR FILTE...

Page 39: ...E MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 HYDRAULIC SYSTEM SCHEMATIC WHEEL LANDING GEAR CONFIGURATION SHOWN FOR EXAMPLE ONLY STANDARD SKID LANDING GEAR CONFIGURATION INCLUDES PROVISION TO ADD WHEEL SUBSYSTEM ...

Page 40: ...ocated immediately in front of each crew door The upper right and lower left static ports provide primary equalized ambient pressure to the airspeed and vertical speed indicators and altimeter through the alternate static source switch PRI position The lower right and upper left ports provide the switch an alternate ambient source ALT position and include provisions to connect to the optional copi...

Page 41: ...ource is provided there in no need for an internal source which could cause inaccurate instrument indications Additionally asecondpitot tube is installed as standard equipment Located on the left side of the nose but not connected internally it is included to facilitate installation of the optional copilot instrument kit The pitot static system is fitted with condensation drains and provisions to ...

Page 42: ...the left copilot section of the panel for the optional copilot flight and navigation instrument kit All aircraft system indications are displayed on the IIDS Integrated Instrument Display System located in the center section for easy observation from either crew seat The center section also contains space for optional avionics control heads arranged for convenient viewing adjustment by pilot or co...

Page 43: ...gical Conditions flight The illustration below shows the normal locations for standard instruments as well as space reserved for selected factory installed options OVERALL INSTRUMENT PANEL LAYOUT SHOWN WITH OPTIONAL EQUIPMENT SHADED STANDARD ELECTROMECHANICAL PILOT INSTRUMENTS Operating limitations areclearly indicated on all electromechanical instruments with green yellow and red bands on the fac...

Page 44: ... face to provide yaw trim indication An ATT FAIL flag is visible when attitude information is unreliable AIRSPEED INDICATOR The airspeed indicator is a standard 3 inch pitot static instrument that indicates the airspeed in knots on a scale graduated from 0 to 180 knots ALTIMETER BAROMETRIC The altimeter a standard 3 inch instrument indicates the altitude of the helicopter from minus 1000 feet to p...

Page 45: ...ent Two adjustment knobs are used to set desired heading and course Warning flags NAV GS HDG appear to indicate unreliable navigation signal or gyro failure HORIZONTAL SITUATION INDICATOR HSI NAVIGATION INDICATORS The vertical speed indicator is a standard 3 inch instrument which shows the rate of climb or descent by sensing the rate of atmospheric pressure change Information is shown in feet per ...

Page 46: ... and eng 1 out RPM eng 2 out display When any of the warning caution annunciators of the IIDS are activated the WARNING or CAUTION or both master caution segment light also illuminates to alert and direct the pilots attention to the panel The press to reset feature extinguishes and rearms the light The RED ENG OUT lights will illuminate whenever the respective engines gas producer speed NG drops b...

Page 47: ...whenever the ROTOR RPM exceeds 105 1 or droops below 93 1 The low ROTOR RPM will also actuate an audio signal to aid the pilot in distinguishing low RPM condition and to warn of possible loss of performance The RPM caution light also incorporates a press to mute feature that silences the audio warning signal RPM CAUTION AND WARNING LIGHTS GLARESHIELD MOUNTED CONTROLS ENGINE START CONTROL PANEL Eng...

Page 48: ...ne FIRE ENG 1 FIRE ENG 2 and a test switch The engine fire extinguishing agent release select switch is located between the two warning lights The RED baggage fire warning light BAG FIRE immediately to the left is of the press to test type The engine FADEC overspeed test panel consists of guarded push on switches for each engine and a TEST toggle switch located on the glareshield The MODE switches...

Page 49: ...y is crisp and clear and does not have any smearing effect which would reduce information legibility The display is consistent and parameter recognition is easy Digit and label size is distinct and easy to read to minimize pilot or crew effort to extract information The IIDS display is fully readable under all ambient display illumination as low as 100 ft lamberts The display has a contrast ratio ...

Page 50: ...th no background or black digits with a yellow background are used to show cautionary conditions and white digits on a red backgroundare used to announce a warning All engine transmission hydraulic temperatures and pressures and electrical indications are displayed on the IIDS along with warning caution and advisory messages Also included is engine and mast torque Q MQ power turbine and main rotor...

Page 51: ...REEN FORMATS 2 UP SCROLLS UP THE WARNING CAUTION ADVISORY WINDOW 3 DN SCROLLS DOWN THE WARNING CAUTION ADVISORY WINDOW 4 C S SELECTS THE CLOCK DISPLAY MODES 5 C C CONTROLS THE CLOCK ET AND ETD RIGHT SIDE CONTROLS 6 SEL SELECTS THE VARIOUS SECONDARY SCREEN FORMATS 7 SWP SWAPS THE PRIMARY AND SECONDARY SCREEN 8 C SELECTS THE COMPOSITE SCREEN FORMATS 9 CHP TRIGGERS THE CHIP FUZZ BURNER OUTPUT 10 TST ...

Page 52: ... of the displays pressing the C switch under the primary display will cause thecomposite screen to be shown IIDS OPERATION FEATURES DUAL DATA INPUT The IIDS receives data for most display parameters from dual sources All operating system data transmitted on the AIRINC 429 data bus is available to the IIDS as well as the corresponding analog input port data for each parameter thermocouple signal mo...

Page 53: ...Y messages available for all display pages will be described as a GROUP immediately following the descriptions of the SYSTEM data displays WARNING CAUTION ADVISORY MESSAGES TRIPLE TACHOMETER The triple tachometer display has three vertical scale displays that simultaneously display rotor RPM NR on the inner scale and engine 1 and 2 NP on the left and right scales Engine and rotor speed data is als...

Page 54: ...ing the descriptions of the SYSTEM data displays OUTSIDE AIR TEMPERATURE Outside air temperature OAT display is a digital format display on page 1 and the START page of the secondary IIDS display The OAT temperature probe protrudes from the underside of the nose The system displays OAT within a range of 60 to 105 degrees C ENGINE OIL TEMPERATURE AND PRESSURE DISPLAYS Both engine oil temperature an...

Page 55: ...nickel cadmium type provides electrical power to keep the clock function active but not displayed whenever normal 28 Volt DC is not available to the IIDS The battery pack is recharged anytime normal electrical power is applied to the airframe The clock modes are as follows Greenwich Mean Time GMT in 24 hour format Local Time LC in 24 hour format Elapsed Time ET count up timer to maximum of 99 hour...

Page 56: ...t vertical scale for each system This data is also presented in digital format The displays are connected to pressure transmitters located on the pressure manifolds and to temperature sensing bulbs on the system reservoirs AUXILIARY FUEL QUANTITY DISPLAY OPTIONAL AUXILIARY fuel quantity if installed is displayed between the hydraulic system displays as a digital total Advisory text shows the posit...

Page 57: ... andADVISORY messages available for all display pages will be described as a GROUP immediately following the descriptions of the SYSTEM data displays COMPOSITE PAGE This display page format is provided in the event one of the dual LCD displays should fail The data shown is a condensed version of that found on the PRIMARY DISPLAY PAGE along with Engine Oil Pressures Transmission Oil Pressure Fuel Q...

Page 58: ... tank START PAGE FORMAT When performing an engine start sequence the secondary page display may be scrolled to the START PAGE which presents expanded scalerepresentations of engine and transmission oil pressure If both engines are running both engines NG above 10 indicated access to this page is inhibited START PAGE DATA UPPER DIGITAL DATA BOX WARNING CAUTION ANNUNCIATOR DISPLAY UPPER GRAPHIC DATA...

Page 59: ...function specified above each key at the bottom edge of the LCD display Using the UP DN and SEL switches will allow the selection of the desired maintenance function while RTN will exit the display to its normal display format Each of the maintenance function displays are MENU DRIVEN with various soft key functions specified above each key at the bottom edge of the LCD display The engine hourmeter...

Page 60: ...includes all warning caution and advisory lights related to the numerous helicopter systems as well as the electrical power and sensors required to operate them With the introduction of the IIDS the old style separate caution panel has been eliminated The IIDS now displays all previously available warning and caution indications provides numerous additional caution warning and advisory indications...

Page 61: ...ages in the warning caution window ADDITIONAL W C MESSAGE ARROW WARNING CAUTION WINDOW SYSTEM AREA W C MESSAGES TYPICAL WARNING CAUTION ADVISORY INDICATIONS DISPLAYS IN THE IIDS SYSTEMS AREA RED AMBER WHITE ECU A RLT 30SEC OEI OPEN aux fuel PRES fuel BUS INT SRT ABT TRANSIT FAIL volt amps CHIP SUMP VALVE ALT O TRQ CHIP SCAV CHIP BRG ECU XMSN OIL C FL SUMP CHIP L R QUILL dash line fuel int C FL SCA...

Page 62: ...e 2 ENG OIL or E OIL 2 Engine2 This warning appears when the engine 2 oil pressure decreases below 52 5 2 5 psig This warning uses the engine 2 oil pressure temperature label annunciator by turning it red and flashing or as E OIL 2 in the W C A window when on page 2 PRES or 1 FU PR Engine 1 This warning appears when the engine 1 fuel pressure decreases below 4 5 1 5 psig The PRES warning appears o...

Page 63: ...e W C A window A ICE 2 This white advisory appears when the engine 2 anti ice system is turned on This advisory appears only into the W C A window AUTO TRIM This caution appears upon AFCS mistrim command This caution appears only into the W C A window SCAS This warning appears when the AFCS failure is declared by the FCC This warning appears only into the W C S window AP This warning appears when ...

Page 64: ...itored by the transmission chip detector in the transmission assembly and the CDPU This caution appears below the xmsn oil temp pressure vertical display or as XMSN CHP in the W C A window when on the secondary screen page 2 This caution appears when a chip detection event has been monitored by the transmission chip detector in the transmission assembly and the CDPU This caution appears below the ...

Page 65: ...ear box chip detection circuit This caution appears below the engine 1 oil temp pressure vertical display or as ENG 1 C FL in the W C A window when on the secondary screen page 2 C FL SUMP or ENG 2 C FL Engine 2 This caution appears when a chip detection failure has been monitored by the CDPU in engine 2 gear box chip detection circuit This caution appears below the engine 2 oil temp pressure vert...

Page 66: ...n appears when a chip detection failure has been monitored by the CDPU in the transmission sump pump chip detector circuit This caution appears below the xmsn oil temp pressure vertical display or as XMSN C FL in the W C A window when on the secondary screen page 2 C FL TAIL RTR or XMSN C FL This caution appears when a chip detection failure has been monitored by the CDPU in the tail rotor chip de...

Page 67: ...engine 1 FADEC ECU sends its degraded mode signal over the ARINC 429 data bus This advisory is enabled whenever a sensor failure will reduce the FADEC ECU response capabilities such as 1 ARINC 429 data bus failure 2 Nr beep fault 3 MGT sensor fault 4 Torque sensor fault 5 Nr sensor fault ECU Engine 1 ECU Engine 2 2 MIN OEI Engine 1 This caution appears when the engine 2 FADEC ECU sends its 2 minut...

Page 68: ... page This caution appears when the engine 1 FADEC ECU sends its 30 second OEI signal over the ARINC 429 data bus This advisory appear on the top left hand side of the primary screen In conjunction with this caution the engine 1 MGT and torque scale change their limit This caution does not trigger the attention getter A flashing down counter is also provided on the left hand side of the No 1 MGT s...

Page 69: ...difference across either side of the filter This caution appears on the left hand side of the fuel tank 2 vertical scale or as FLTR 2 in the W C A window when on the secondary screen page 2 or on the start page FLTR or FLTR 2 This warning appears when the baggage fire warning is triggered by the baggage compartment smoke detector 7 to 10 below that of clean air This warning appears into the W C A ...

Page 70: ...t 54 5 C 130 F condition in the right windshield heater circuit This caution appears only into the W C A window This caution appears when an Ng overspeed has been detected by the engine 1 FADEC ECU Ng 106 This caution appears above the engine 1 Ng digital readout PARK BRK This caution appears when the parking brake is on This caution appears only in the W C A window This white advisory appears whe...

Page 71: ... appears only into the W C A window SRT ABT Engine 1 M ECU 2 Engine 2 This caution appears when engine 2 FADEC ECU is performing an auto relight sequence by powering the ignition exciters on engine 1 This caution appears above engine 2 torque display on the primary screen This white advisory appears when engine 1 FADEC ECU has detected a soft fault and the PLA is below ground idle on engine 1 This...

Page 72: ...t changes state from a failure signal or chip signal the CDPU will interrupt the individual signal and resend it with the proper recognition of the occurrence for the IIDS The CDPU will either accept a ground input for system self test or be able to self test upon power up The test sequence will last about 6 seconds and trigger one chip signal for each engine and one for the transmission The CDPU ...

Page 73: ...D DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ELECTRICAL POWER DISTRIBUTION SCHEMATIC ...

Page 74: ... the loss of its DC bus but not the loss of its emergency bus which is interconnected to the opposite emergency bus The failed DC bus may have power restored by activating the bus interconnect relay BUS INTCON switch FAULT PROTECTION The bus interconnect relay is inhibited from closing if a bus feeder fault short circuit exists This is to prevent connection of the operative generator to a faulty c...

Page 75: ...s the battery is sized to provide a minimum of 30 minutes operation when poweringonly the two emergency buses Power may be restored to the DC BUSES using the battery as source but a reduced operating time will result The battery contains three temperature sensors two provide input to the IIDS warning and caution displays while one monitors temperature during external power operation battery chargi...

Page 76: ...rs of Subsystem 1 on the left and Subsystem 2 on the right Five rocker type switches at the consoles central forward edge control the Battery Generator 1 2 the Inverter and theEmergency Light The rocker switches are clearly labeled and internally illuminated with white light Except for the DC bus controlswitches white illuminated the remaining push on push off switches change illumination color fr...

Page 77: ...ncluded for dimming the optional copilot instruments One cockpit utility light with red white spot flood beam Two map lights One cockpit emergency light Internal white instrument lights Storm Lights external instrument illumination Pedestal equipment lighting Overhead console lighting Four cabin dome lights with integral battery powered emergency lights Four luminescent panels over each emergency ...

Page 78: ...d by a switch CABIN BAG LT on the overhead console their intensity can be adjusted by the pilot Each dome light contains a separate battery powered emergency light controlled by the EMERGENCY LIGHT SWITCH Two Ni Cad batteries one each for the two left and two rightlights are kept fully charged by the electrical system Activation is automatic when the system is armed and both emergency buses fail T...

Page 79: ... green light on the right wing a red light on the left wing and a white light on the tail ANTI COLLISION LIGHTS Two highly conspicuous red strobe lights serve to draw attention in flight or on the ground One is located above the engine cowling and another is found on the underside of the tail boom SEARCH LANDING LIGHT The search and landing light is a single high intensity 450 watt wide beam direc...

Page 80: ...r in varies the door opening upper knob or diverts airflow lower knob to the defog nozzle Releasing the center of the knob locks the cables position The vent nozzles located on either side of the instrument panel may be adjusted for direction and volume Each system will function with ram air only or for ground hovering operation with the vent blowers PILOT VENT BLO CPLT VENT BLO switches on the ov...

Page 81: ...UMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 UPPER CABLE CONTROL OPENS PLENUM DOOR VENT OUTLET ROTATE CLOCKWISE TO CLOSE COUNTER CLOCKWISE TO OPEN LOWER CABLE CONTROL DIVERTS AIRFLOW TO DEFOG DEFOG NOZZLES PROVISION FOR OPTIONAL ECU BLEED AIR HEAT ...

Page 82: ...the four cabin lights with two additional outlets just above the windshields in front of the pilot and forward passenger Each of the outlets is separately controllable in direction and volume Air exhausts from the cabin through two ports left and right near the floor at the lower edge of the rear bench seat The ports may be opened or closed by hand to help adjust the flow The minimum cabin air exc...

Page 83: ...de designated ENGINE NO 1 and the right side as ENGINE NO 2 Optimized for performance under hot day high altitude conditions there is ample reserve power contained in each compact 118 kilogram 260 pound unit POWERPLANT TWO ROLLS ROYCE 250 C40B TURBOSHAFT ENGINES ENGINE RATINGS Rolls Royce 250 C40B with Full Authority Digital Electronic Control FADEC Takeoff Power 5 Minutes SHP kW 808 603 747 557 M...

Page 84: ...le module can be accomplished independently The compressor for instance may be removed for repair or overhaul while the remainder of the engine continues in service with a replacement overhaul exchange unit temporary leased compressor MODULAR CONSTRUCTION RELIABLE POWER Manufactured by Rolls Royce the C40B is one of the latest in the evolutionary Model 250 series which has amassed over 100 million...

Page 85: ...OR MODULE SIMPLE ONE PIECE OUTER COMBUSTOR SINGLE COMBUSTOR LINER SINGLE FUEL NOZZLE SINGLE SPLIT LINE FOR REMOVAL FROM TURBINE COMPLETE COMBUSTOR SYSTEM HARDWARE CAN BE INSPECTED BY REMOVAL OF COMBUSTOR MODULE GEARBOX MODULE READY FOR OVERHAUL OR REPAIR BY REMOVING SIX GEARBOX MOUNTING BOLTS SIMPLE SINGLE STAGE IMPELLER NO VARIABLE GEOMETRY MOUNTED TO THE REAR OF THE GEARBOX WITH FIVE NUTS FIRST ...

Page 86: ... C40B engine is quite simple continuous combustion that produces a steady flow of efficient power Air is supplied to each engine through airscoops on either side of the fuselage aft of the transmission cowling Airflow at takeoff power is approximately 2 54 kilograms per second 5 6 pounds per second for each engine Before the air enters the engine it passes through a protective screen to prevent th...

Page 87: ...SSOR SECTION Clean air enters the compressor inlet The compressor in the C40B is a titanium single stage centrifugal impeller which compresses the entering air 8 6 to 1 pressure ratio at takeoff power and discharges it through a diffuser assemblyand dual scroll collector into a pair of external ducts The ducts carry the air directly to the combustion section at the aft end of the engine EXAMPLE BL...

Page 88: ...m consists of a pneumatically operated bleed valve and an inducer bleed assembly As NG increases the bleed valve gradually closes to reserve air for engine operation The inducer bleed serves a similar function to enhance compressor efficiency when NG is above 96 Four ports along the diffuser scroll are provided to supply bleed air One provides air to the engine fuel system a second is for to the a...

Page 89: ...n the compressor scroll controls the air flow Anti icing ON is required when flying into visible moisture at temperatures below 4 5 C 40 F ANTI ICING SYSTEM A compressor wash rinse fitting is provided to facilitate the recommended daily compressor cleaning to remove airborne chemical contamination such as when operating near salt water A spray nozzle connecting tubing and threaded adapter are inst...

Page 90: ...COPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ACCESSORY GEARBOX SECTION The accessory gearbox section includes a gearbox housing FRONT or COMPRESSOR side a gearbox cover REAR or TURBINE side gas producer gear train power turbine gear train oil pump assembly oil filter and the necessary oil tubes to provide pressure and scavenge oil for the system ...

Page 91: ...AFT 4 SPUR IDLER GEARSHAFT 5 SPUR HYDRO MECHANICAL UNIT OIL PUMP NG TACH GEARSHAFT 6 GENERATOR IDLER GEAR 7 STARTER GENERATOR GEARSHAFT 1 4 5 7 2 3 TURBINE TO COMPRESSOR COUPLING SPARE STARTER GENERATOR DRIVE 6 DRIVES FADEC H M U ENGINE OIL PUMP NG TACHOMETER GAS PRODUCER GEARING The accessory drive train is powered by the gas producer turbine It drives is driven by the starter generator and provi...

Page 92: ...o the main forward output drive at a design speed of 9 598 RPM In addition the rear side of the main output drive provides power to operate the airframe mounted oil cooler blower POWER TURBINE GEARING LEFT IS FORWARD DRIVES P M A 8 HELICAL POWERTRAIN DRIVE GEAR 9 HELICAL TORQUEMETER GEARSHAFT 10 HELICAL POWER TAKEOFF GEARSHAFT 11 SPUR POWERTRAIN IDLER GEAR 12 SPUR POWERTRAIN PERMANENT MAGNET ALTER...

Page 93: ...nsists of an outer case a combustion liner an igniter and a fuel injector The prechamber combustion system is designed to burn fuel at peak efficiency and to minimize emissions Fuel is sprayed into the chamber at a precisely controlled rate The single igniter produces a constant spark while the start circuit is energized until automatic starter disengage at 58 NG Gas flow moves forward out of the ...

Page 94: ...used for engine cooling and thrust balance The cooling air is directed into the combustion liner to prevent the flame from contacting the liner wall and to cooling air passages in the gas producer turbine support the turbine nozzles and the first stage nozzle shield Some of the high pressure cooling air is delivered to the thrust balance chamber at the forward face of the second stage gas producer...

Page 95: ...turbine and exhaust collector supports are high temperature resistant structures which house support and thrust bearings oil and air seals passages for lubrication cooling air and thrust balance air temperature sensing thermocouples and the outer casings which connect the combustion section and the accessory gearbox The two turbine units are free to revolve independently of one another Each turbin...

Page 96: ...UARY 2003 The first two turbine stages are coupled to the compressor and also power the gas producer gear train At 100 RPM they rotate at51 000 RPM The gas producer support contains a protective energy containment ring which surrounds the first stage gas producer turbine wheel The energy ring guards against damage from ballistic fragments in the event of a turbine wheel failure GAS PRODUCER TURBIN...

Page 97: ...s to drive the power turbine At 100 RPM the power turbine rotates at 30 908 RPM The power turbine support incorporates a thermocouple assembly which senses the temperature of the combustion gases as they exit the second stage gas producer rotor Four ALUMEL CHROMEL probes generate a DC current directly proportional to the temperature of the gas The thermocouple harness averages the four voltages an...

Page 98: ...castings The exhaust collector support holds the aft portions of the engine and is attached to the accessory gearbox cover with six studs The exhaust collector duct incorporates a center tube and power turbine shaft shield which protects the power turbine shaft from the exhaust gas The duct has a single rectangular outlet at its top which supports the exhaust ejector stack The vertical firewall sh...

Page 99: ...AY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ENGINE ACCESSORIES CONTROLS CEFA COMBINED ENGINE FILTER ASSEMBLY HYDROMECHANICAL UNIT PERMANENT MAGNET ALTERNATOR ...

Page 100: ...n assisted by dedicated air inlets on the lower outboard engine cowlings ENGINE START CONTROL PANEL Engine starting is controlled by three push push illuminated switches mounted above the engine instruments group When the START 1 or START 2 switches are engaged the starter is continuously motored until automatic disengagement occurs at 56 N G or the center START DISENG switch is depressed The IIDS...

Page 101: ...costs 6 Simplify engine maintenance and trouble shooting The FADEC fuel and control system consists of 1 Hydromechanical Unit HMU 2 Fuel filter oil filter assembly CEFA 3 Electronic Control Unit ECU 4 Permanent Magnet Alternator PMA 5 Compressor inlet air temperature sensor inlet duet mounted 6 P1 compressor air inlet pressure sensor in the ECU 7 Engine sensors of RPM MGT and Torque 8 Aircraft sup...

Page 102: ...tatus to the aircraft The Hydromechanical Unit consists of the dual element fuel pump fuel metering valve manual fuel control three solenoid valves two check valves a fuel shutoff valve with a pilot valve windmill bypass valve bypassing type pressure differential regulator valve power lever input shaft and two feedback potentiometers During automatic operation of the FADEC fuel metering by the HMU...

Page 103: ...g operation include 1 Improved power turbine governing 2 Torque limiting 3 MGT limiting 4 Constant transients insensitive to fuel type temperature and metering inconsistencies 5 Improved autorotation recoupling minimizes rotor RPM droop 6 Surge detection recovering avoidance Advantages regarding safety include 1 Improved overall engine reliability 2 High reliability electronics 3 Dual channel NP o...

Page 104: ...NP governing at flight idle Normal flight operations shall be conducted with the throttle twist grip at 100 travel If desired the PLA throttle can be rolled back to force a power turbine speed helicopter rotor speed NP NR needle split for autorotation training POWER TURBINE NP GOVERNOR The ECU governs NP to maintain helicopter rotor speed NR at the set point The control utilizes isochronous speed ...

Page 105: ...er a minimum NDOT or increasing MGT is established No pilot action is required unless the engine fails to relight by 50 gas generator speed NG In the event of an unsuccessful relight the engine PLA throttle should be moved to cutoff AUTORELIGHT The FADEC detects engine surge by comparing the rate of change of NG speed to a predetermined boundary rate If the boundary is exceeded and MGT is increasi...

Page 106: ... first turned on This check ensures electrical continuity of the overspeed circuit and the ability of the ECU to power the overspeed solenoid This test is performed by turning on each of the overspeed solenoid drivers and measuring the voltage and current draw across the overspeed solenoid valve The measured voltage and current are then compared to limits Power turbine overspeed limiting is provid...

Page 107: ... be recorded by the ECU s EMS feature FAILURE ENUNCIATION In auto mode a software implemented overspeed system is provided Should the software detect an NG speed above the NG overspeed threshold the ECU will activate the overspeed solenoid valve and reduce fuel flow to minimum flow Once the NG speed drops below the overspeed threshold the solenoid valve opens and normal operation may resume The EC...

Page 108: ...tionally the fuel flow slew rate is mechanically limited to avoid blowout and to provide proper responsiveness for aircraft operation ARINC 429 DATA BUS The ECU provides a transmit only ARINC 429 data bus This data bus contains engine parameters such as NG speed NP speed MGT and torque ENGINE FAULT ANNUNCIATORS There are eleven warning caution annunciations included in the IIDS that AUTOMATIC ENGI...

Page 109: ... for aircraft torque sensing on the accessory gearbox The ignition exciter is a solid state high energy ignition unit The unit is designed to have a constant spark rate of 300 to 330 sparks per minute throughout its operational temperature and voltage range The exciter is energized when either the PLA is greater than 9 and NG is between 5 and 50 the anti ice is selected a flameout is detected IGNI...

Page 110: ... located on top of the aft fuselage section Each engine is attached by three stainless steel bipod mounts which feature replaceable bearings and master shims for proper alignment Each forward bipod pair supports one engine gearbox while the aft bipods support their respective engines turbine to combustor flange AFT FIREWALL CENTER FIREWALL FORWARD FIREWALL TAIL ROTOR DRIVE TUNNEL OIL COOLER BLOWER...

Page 111: ...r the engine cowlings The forward firewall istitanium reinforced with fireproof composite honeycomb and with aluminum cowl frames The center sections are titanium and provide a protective housing for the tail rotor drive shaft the transmission oil lines and are easily removed for access to the inboard sides of the engines CENTER FIREWALLS REMOVED INBOARD ENGINE BIPOD MOUNTS TRANSMISSION OIL LINES ...

Page 112: ...ECTION Powerplant fire detection is accomplished by two independent continuous loop detection systems one on each engine compartments engine deck Each system has a warning light and test switch Resistance of the semi conductor detection element decreases with temperature rise which allows current to flow between the wire conductor and the stainless steel tube illuminating the engine fire warning l...

Page 113: ...ers 60 cubic inches of Halon charged with 4 134 kPa 600 psi nitrogen Electrically activated squibs permit each bottles contents to be directed into either engine compartment In the event of an engine fire warning indication ARMING that engines system will automatically close the selected engines fuel shut off valve and bleed air valve and connect the AGENT RELEASE switch to both bottles discharge ...

Page 114: ...chamber which stabilizes and directs the airflow to the engines air inlet Protective screens are mounted to the front side of the forward firewall to prevent ingestion of debris There is adequate space inside the plenums to replace the screens with the optional engine air particle separator kit when operations are conducted in dusty environments ENGINE AIR INTAKES Air intakes are provided for engi...

Page 115: ...gh the ejectors is cooling air drawn from the engine compartments Two air intakes are built into each lower engine cowl to provide air for cooling The rear inlets supply air to the oil cooler blowers while the forward inlets direct ambient air onto the engine gearbox cover mounted accessories Airflow through each engine compartment is provided by the action of the exhaust ejection system ENGINE CO...

Page 116: ...VE PRODUCT DATA JANUARY 2003 ENGINE OIL SYSTEM A separate and independent oil system is installed for each engine Each system is comprised of a cooler an oil tank two engine chip detectors and an engine mounted oil filter Cooling of engine oil is accomplished by two engine driven axial blowers HEAT EXCHANGER TRANSITION DUCT SHAFT DRIVEN BLOWER EACH ENGINE HAS INDEPENDENT OIL SYSTEMS ...

Page 117: ...NT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ENGINE OIL SYSTEM SCHEMATIC DIAGRAM ROLLS ROYCE 250 C40B ...

Page 118: ...gine The blowers are isolated from the engine compartment by their own firewalls OIL COOLER BLOWER OIL TANKS The engine oil tanks are located on the front side of the forward firewall one on each side just below the engine air inlets Each tank has a fluid level indicator and filler cap which are easily accessible through a hinged panel for inspection and servicing Each system has a capacity of 6 4...

Page 119: ...The oil cooler and external filter for each engine is located behind the aft firewall The coolers oil inlet incorporates a thermostatic valve which allows the oil to bypass the cooler until optimum operating temperature is reached A separate portion of the heat exchange core also receives transmission oil for cooling One half of the transmission oil is cooled by each heat exchanger ENGINE TRANSMIS...

Page 120: ...from the thrust generated by the torquemeter gear shaft A pressure transducer provides information to the AIRINC 429 databus which is used by the IIDS to indicate engine torque on the respective scale of the triple torque display and in engine torque matching Each engines oil is monitored in two places for metal particles by electric magnetic detectors The ENG SUMP plugs monitor the accessory gear...

Page 121: ...the fuselage are designed to stretch up to 50 Each fuel compartment is lined with a flexible bladder constructed of a multilayered sandwich type laminationof rubber cement nylon and woven fabric All cells have met rupture resistant standards by being drop tested from 15 meters 50 feet while 75 full with no subsequent leakage The E 1622 2 cell liner material features a 16 gauge gum rubber inner lin...

Page 122: ...ot affect both engines An interconnect valve assures that all fuel is available for single engine operation An electrical fuel shutoff valve for each engine is located on the forward firewall A thermal relief valve permits the return of fuel to the feed tanks after shutdown removing internal pressure from the engine fuel controls Each feed tank incorporates a sump drain and prime pump assembly The...

Page 123: ...to the rear by a gutter just above the wing fuselage joint The Bell 430 basic fuel system can be refuelled through its single filler port at the maximum flow rate of 114 liters per minute 30 U S Gallons per minute REFUELLING A fuel temperature sensor is located in the No 2 left prime pump assembly The sensor provides data to the IIDS which displays fuel temperature on the START PAGE The display in...

Page 124: ...played on the IIDS warning caution window indicate low pressure at the engine driven pumps engine mounted filter clogged fuel shutoff valve malfunction on when valve and switch disagree fuel tank interconnect valve position on for open and low fuel quantity in either both feed tanks less than 41 4 5 kilograms 90 10 pounds Two thermistors one in each sump assembly control the two LOW FUEL indicatio...

Page 125: ...pter OVERTEMPERATURE INDICATORS Power is supplied to the transmission through two main drive shafts Each shaft has a flexible splined coupling at either end which allows for variations in alignment caused by normal motions of the transmission The dynamically balanced shafts pass through the forward firewall inside quick disconnect baffle assemblies which maintain the required isolation of the engi...

Page 126: ...ansmission is mounted on the cabin roof just forward of the power plant It accepts and combines power from the two engines to drive the main and tail rotors Each outboard power input quill sometimes referred to as KNUCKLE incorporates a sprag type freewheeling clutch to permits single engine operation An inoperative engine does not become a burden as the other engine takes automatic action to comp...

Page 127: ...ight input pinion gears The outboard gear assemblies incorporate the freewheeling clutches sprag clutches whose internal shafts connect to and drive the hydraulic pumps The second reduction stage is through the main spiral bevel collector gear which combines the power from both inputs and also powers the tail rotor output gear The third reduction stage is through a high contact ratio planetary gea...

Page 128: ...ICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 1 Input pinion gear 2 2 Outboard gear assembly 2 3 Freewheeling clutch 2 4 Spiral bevel collector gear 5 Collector gear shaft 6 Tail rotor drive gear 7 Oil pump drive gear 8 Sun gear 9 Pinion gear 6 10 Ring gear 11 Planetary carrier 12 Main rotor mast 13 Hydraulic pump drive 2 TRANSMISSION SCHEMATIC ...

Page 129: ...uce airframe vibrations The elastomeric pads at the transmission fittings provide vertical softness Transmission pitch and roll restraint and the allowable motion envelope are controlled by dual FWD AFT and LATERAL elastomeric dampers Each isolation mount has a visual inspection port which permits observation of the correct fluid level within the sealed assembly LIVE PYLON INSTALLATION This transm...

Page 130: ...ccomplished by comparing the difference between each lift link s electronic signal The four signals are conditioned processed and displayed on the IIDS Integrated Instrument Display System MAST TORQUE INDICATION TRANSMISSION POWER RATING The primary reference to power levels is through torque based loads in the transmission struts with both engines operating When one engine is inoperative the refe...

Page 131: ... long in service life The system is accessible by decowling and through a removable panel in the interior cabin roof SYSTEM ACCESS AFT PYLON MOUNTS FITTINGS FOR UP STOP STRIKE PLATES BOTH SIDES FWD PYLON MOUNTS FWD LAT RESTRAINT ATTACH REMOVABLE PANEL Two spike and up stop assemblies are located on the isolation mount fittings on either side of the transmissions base The spikes extend into the upp...

Page 132: ...uted to the eight main jets for delivery to the gears and bearings Each of the removable jets are internally screened to prevent foreign material from blocking the oil spray The filter incorporates a bypass valve which opens if back pressure occurs due to cold temperature or clogged filter The oil manifold contains an oil temperature switch and bulb and an oil pressure transmitter TRANSMISSION LUB...

Page 133: ...e IIDS is illuminated An oil temperature bulb and an oil pressure transducer provide temperature and pressure signals to the IIDS Six chip detectors are located in the transmission to provide both warning and diagnostic information The two upper detectors monitor theupper mast bearings and the planetary gears and bearings Chip collectors prevent secondary contamination of the transmission and isol...

Page 134: ...NTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 TRANSMISSION OIL SCHEMATIC ...

Page 135: ...ny inputs caused by the normal range of pylon motion Transmission oil cooling takes place inboth of the engine oil coolers heat exchange cores This insures than even with only one engine operating the transmission oil will be cooled The oil lines from the transmission to the coolers pass along the central firewall tunnel of the engine compartment OIL COOLER The rotor brake shortens the time requir...

Page 136: ...r RPMhas decreased to 55 Stops have been demonstrated in winds up to 111 km hr 60 knots ROTOR BRAKE OPERATION The rotor brake is activated by its own independent hydraulic system The handle and cylinder are located on the control tunnel wall to the right of the pilot while the system fluid reservoir is located on the cabin roof When engaged two RED caution lights in the main caution panel illumina...

Page 137: ...rier to provide the mast drive source The center splines are master splined and drive the rotating portion of the swashplate The upper splines and flange drive the main rotor The mast is mounted to the top of the transmission and extends downward through the transmission into the mast alignment bearing The mast is supported in the transmission by a single ball bearing bearing liner and retainer Th...

Page 138: ...mission and receive control input from the servo actuators Collective servo input through the collective levers raises or lowers the swashplate ball sleeve which results in an equal increase or decrease in the pitch of the blades The left and right cyclic servo actuators inputtilts the swashplate to effect differential pitch in each of the rotor blades causing the rotor system to tilt in the direc...

Page 139: ...in the mast flange and the mast drive adapter Four upper damper stops and four lower damper stops limit the flapping of the rotor system Pitch horns are attached to adapters which also mount the fluid filled lead and lag dampers and are attached to the main rotor blades by four bolts The main rotor carries centrifugal and bending loads flapping and lead lag through the sets of composite yokes They...

Page 140: ...IVE PRODUCT DATA JANUARY 2003 Coning and flapping stops are provided to prevent yoke damage in gusty wind conditions Anti fretting pads and coatings are used to improve durability The pair of yokes are bolted to an integral flange on the mast This arrangement is simple and makes it easier to maintain the quality of the ride FLANGED MAST STACKED YOKES PITCH CHANGE ADAPTER PITCH HORN ...

Page 141: ...on The main rotor blades have a rectangle planform with thickness that tapers down to 6 at the tip to reduce noise This thickness tapering reduces noise almost as much as a swept tip does while retaining the simplicity of design and construction that helps control the cost of a blade Parameters of the main rotor are Diameter 42 feet 12 8 meters Blade chord 14 2 inches 0 36 meters Tip speed 765 ft ...

Page 142: ...ED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 MAIN ROTOR BLADE CONSTRUCTION FEATURES ...

Page 143: ...ed for lubrication The two yoke flexures are mounted on top of each other to form a stacked four bladed rotor system The yokes are mounted directly to the mast flange with a dowel pin located on the flange to position the lower yoke The upper yoke will then mount 90 on top of the lower yoke The drive plate assembly mates with splines on top of the mast aligned with a match mark on the top of the m...

Page 144: ... each yoke houses an elastomeric shear restraint and two elastomeric lead lag dampers Lord has designed the elastomeric components for on condition replacement and a 5000 hour fatigue life Dampers can be replaced without disconnecting the pitch links or removing the blades No measurement or shimming is required SHEAR RESTRAINT PITCH CHANGE ADAPTER LEAD LAG DAMPERS ELASTOMERIC DAMPERS SHEAR RESTRAI...

Page 145: ...aring assembly The pitch link may be adjusted to correct out of track andautorotation rotor R P M It transmits movement from the driven assembly of the swashplate to the main rotor hub pitch horns to regulate the pitch angle of the main rotor blades The pitch links are repairable by replacement of the universal bearing and or clevises A lubrication fitting is provided in upper end of link and shou...

Page 146: ...fts are interchangeable The tail rotor drive shafts are supported and interconnected by three hanger bearing assemblies Each assembly consists of two attachment adapters on a short splined shaft through a single row sealed ball bearing in a ring shaped hanger equipped with four mounting lugs for attachment to their support fitting Each hanger bearing has a redundant safety strap retainer which mai...

Page 147: ...TROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 TAIL ROTOR DRIVE INSTALLATION ...

Page 148: ...CT DATA JANUARY 2003 HANGER BEARING THOMAS COUPLING INSTALLATION THOMAS COUPLING INSTALLATION 1 Hanger Support 2 Safety strap retainer 3 Hanger adapter 4 Driveshaft segments 2 3 4 5 Radius washer 6 Disc assembly 7 Hanger adapter 8 Radius washer HANGER BEARING ASSEMBLY 1 Forward adapter 2 Bearing 3 Hanger 4 Spring 5 Spacer 6 Nut 7 Nut 8 Locknut 9 Aft adapter EXAMPLE ILLUSTRATION EXAMPLE PHOTO ...

Page 149: ...type lubrication system The gearbox is also equipped with a vented oil filler cap an oil level sight glass and a drain plug chip detector FUZZ burning for ease of maintenance and inspection TAIL ROTOR The tail rotor counteracts the torque of the main rotor and functions to maintain or change the helicopters heading by means of the control linkage from the pilot s directional control pedals The tai...

Page 150: ...p a balance wheel and two pitch links Upper and lower extensions on either side of the yoke serve as blade grips The hub attaches to the tail rotor output shaft by means of the trunnion which is roller bearing mounted about the flapping axis The tail rotor has collective pitch control only Control inputs enter the rotating system by an annular contact bearing set on the gearbox output shaft Active...

Page 151: ...DE The tail rotor blades are bonded assemblies consisting of shaped stainless steel spars with an aluminum honeycomb core covered by stainless steel skin Two spherical non lubricated bearings at the base of each blade are used for blade retention and pitch change The high efficiency airfoil permits a low operating speed 1881 RPM which keeps noise to a minimum and reduces theerosion effect of opera...

Page 152: ...EN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 AIRFRAME Six major component subassemblies comprise the 430 airframe Forward fuselage Aft fuselage Tailboom Wings Cowling Landing gear ...

Page 153: ...duce maintenance requirements and enhance the overall appearance of the helicopter by presenting smooth contours Protection against corrosive elements and galvanic action is provided by a coating of epoxy polyamide primer All panel edges and fiberglass surfaces are sealed and spot welding is NOT used The exterior surface of the helicopter is further protected by very durable polyurethane paint FUS...

Page 154: ...d doors A main and an interface bulkhead where the aft structures attach give the cabin rollover protection The forward cross tube of the skid landing gear mounts to the bottom of the main bulkhead The bulkheads are of the box type which permits their use for duct and wiring installation without encroaching on passenger space The nose forms the avionics radar compartment The nose section dooropens...

Page 155: ...copter just behind the wing It has a handle and keyed lock which are identical to those on the cabin doors There is a hinged removable partition at the front of the baggage compartment which may be lifted up and locked in position or removed when large cargo is transported SIDE STEP WORK PLATFORMS AFT FUSELAGE The aft fuselage is spliced to the forward fuselage at the interface bulkhead It include...

Page 156: ...ting There is an additional space located behind the aft baggage compartment wall which may be used for optional avionics components Two vibration absorbers FRAHM DAMPERS are located in the fuselage They are positioned on the cockpit floor one outboard of each crew seat The sealed units consists of an oscillating weight dampened by springs and limited in travel by snubbing bumpers In operation the...

Page 157: ...rally located on the outboard surface Both wings include structural provisions for mounting the optional emergency flotation systems float assemblies which fit beneath the wing caps when installed Each wing contains a rupture resistant fuel cell which is connected to the internal fuel cell feed and vent lines through self sealing break away fittings A portion of the upper surface of each wing serv...

Page 158: ...losed inside the tail boom Access doors allow easy inspection The vertical fin sweeps back both above and below the end of the tail boom It is canted to the right to reduce the tail rotor thrust required for forward flight A dual surface trailing edge flap Gurney flap is attached to the fin to prevent washout of the vertical surface when bank angle exceeds 30 and to increase efficiency in normal f...

Page 159: ...zer provides pitch stability for the helicopter Leading edge slats are incorporated for improved pitch stability Auxiliary vertical fins are attached to the outboard tips of the stabilizer which provide improved directional stability for small yaw angles and improved dihedral stability A two section cover extends along the top surface of the tail boom to protect the driveshafts It is attached to f...

Page 160: ...e assembly with access inspection doors on each side which is fabricated of light weight aluminum alloy The transmission cowling is a single piece aluminum honeycomb alloy unit which is attached to the fuselage by quick release DZUS fastener screws Access doors located on each side just above the cabin doors allow inspection of the hydraulic system modules and access to the maintenance platforms o...

Page 161: ...ttach to the engine firewalls with DZUS type fasteners to form part of the engines exhaust ejector system The left and right lower engine cowlings are light weight fireproof graphite composite assemblies hinged at the top and secured at the bottom with positive locking latches When opened the lower cowlings are supported at a 100 position by tubular gust lock struts The two section aft fairing cov...

Page 162: ...imple light weight and practically maintenance free It is designed to absorb energy and to preclude damage to the airframe in the event of a hard landing The gear is designed for energy attenuation of descent speeds up to 2 0 meters per second 6 55 feet per second by elastic deflection of the forward and aft cross tubes Yielding of the crosstubes beyond normal operating limits in combination with ...

Page 163: ...e by four straps which bolt to fittings located on the two main bulkheads A step is provided at the forward end of each skid along with a tow ring for ground handling Two eyebolts are provided on each skid near the helicopters center of gravity for attachment of the dual ground handling wheels Each skid is fitted with a three section replaceable wear shoe assembly which protects the skid tube from...

Page 164: ...DUCT DATA JANUARY 2003 AIRFRAME FEATURES STEPS AND GRIPS Access to the top of the helicopter is quick and easy with the steps and grips provided on both sides of the fuselage All the steps are coated with a non slip material for secure footing The work platforms located on the cabin roof and the wing surfaces allow rapid and easy completion of the pilots preflight inspection WORK PLATFORMS ...

Page 165: ... in the floor panels which provide for the various seat configurations They accept attachment of either the seat frame collets or optional stud adapters which may be fitted with cargo tie down rings Each of the recessed studs is stressed for ultimate loading of 2155 kilograms 4750 pounds vertical and 700 kilograms 1545 pounds horizontal The normal floor loading limit is 488 kilograms meter 100 pou...

Page 166: ...he right side of the helicopter near the fuel filler cap Within the baggage compartment there are 12 Footman loops tie downs located around the perimeter of the load bearing panel They are stressed for an ultimate load limit of 499 kilograms 1100 pounds in any direction The baggage compartment structural maximum load is 227 kilograms 500 pounds with a deck loading limit of 448 2 KG M2 100 LBS FT2 ...

Page 167: ...UARY 2003 Additional equipment access locations within the interior of the helicopter and under the fuselage may be found in the 430 Maintenance Manual MAIN ACCESS DOORS PANELS Various doors and panels are located throughout the fuselage to allow access for maintenance and servicing of the helicopters systems Some panels are structural load carrying members and are required for ground run and or f...

Page 168: ...AN UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 DOORS WINDOWS ...

Page 169: ...edown assemblies and atail rotor tiedown strap Three fittings are located on the underside of the helicopter for the attachment of a clevis and tiedown lines It is recommended that the helicopter be moored to prevent damage during periods of high wind and turbulent weather or whenever the forecast wind velocity exceeds 93 km hr 50 knots If the forecast wind velocity exceeds 134 km hr 75 knots the ...

Page 170: ...OM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 COVERS AND PLUGS Covers for the engine air and oil cooler blower inlets engine exhausts and the pitot tubes are included in loose equipment Use of covers whenever the helicopter is left unattended is recommended to prevent foreign object damage FOLDING BLADE SOCK WAND ...

Page 171: ...at is capable of lifting the entire helicopter An additional procedure is listed in the Maintenance Manual for lifting the helicopter with the transmission removed MAXIMUM Gross Weight for lifting the helicopter is limited to 6900 pounds HOISTING JACKING AND LEVELING The helicopter is fitted with threejack pads and a leveling plate which are used to measure aircraft weight and center of gravity Th...

Page 172: ...eels are extended into the moving position by means of a hand operated hydraulic pump in the supporting cradle of each unit The wheels weigh a total of 70 kilograms 154 pounds and must be removed prior to flight The maximum approved weight for towing the standard skid gear equipped helicopter is 3175 kilograms 7000 pounds Towing the helicopter over an unprepared surfaces or across hanger door trac...

Page 173: ...icated as a Stage 2 helicopter as prescribed in FAR Part 36 Subpart H for gross weights up to and including the maximum takeoff and landing weight of 4091 kilograms 9000 pounds There are NO operating limitations in meeting the takeoff flyover or approach noise limit requirements CERTIFICATED FAR PART 36 STAGE 2 EXTERNAL NOISE LEVELS FLIGHT CONDITION EPNL EPN DB TAKEOFF 92 4 FLYOVER 91 6 APPROACH 9...

Page 174: ...HIS IS AN UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ...

Page 175: ...S ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 SECTION TWO OPTIONAL EQUIPMENT FACTORY INSTALLED BHTC VENDOR STC KITS ...

Page 176: ...HIS IS AN UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ...

Page 177: ...FC 500 SINGLE AFCS 204 KFC 500 DUAL AFCS 205 COPILOT INSTRUMENTS 206 STANDBY ATTITUDE INDICATOR 207 DUAL CONTROLS 208 COPILOT INTERCOM SYSTEM 209 KING GOLD CROWN III PROVISIONS 210 NO 2 VHF AM COMMUNICATION TRANSCEIVER 211 NO 1 NAV ILS MARKER BEACON RECEIVER 212 NO 2 NAV ILS COURSE DEVIATION INDICATOR 212 AUTOMATIC DIRECTION FINDER 213 DISTANCE MEASURING EQUIPMENT 214 TRANSPONDER MODE S ENCODING A...

Page 178: ...d configuration weight after installation has been completed Depending on final helicopter configuration and ballast required the actual weight increase may be more or less In addition to the Bell kits listed in this section as factory or customer installed optional equipment several FAA approved optional kits have been built by other companies Normally customers desiring installation of these kit...

Page 179: ...the waters surface in the event of emergency ditching Two kits are available one for the SKID landing gear configuration and one for the WHEEL landing gear configuration Each kit consists of four multi compartment float assemblies an inflation system an electricalactuation system a mechanical back up actuation system tailboom sealing modifications to make it watertight provisions for underseat sto...

Page 180: ...ft end of the baggage compartment The primary electrical actuation system consists of four immersion switch assemblies mounted on the belly of the helicopter Activation will occur when the system is armed and any two of the switches are submerged in water a solenoid valve releases the compressed nitrogen gas to pop out and inflate each of the floats Arming of the system is accomplished with a pede...

Page 181: ...in five compartments With any one float compartment deflated the helicopter should generally be stable in the water up to Sea State 2 with wind at 12 knots Sea State 2 is defined as a condition where wind speed is between 10 and 13 5 knots with average wave heights between 0 2 and 1 0 meters 0 8 and 3 3 feet Operating procedures for the Emergency Float Kit are found in the FAA Approved Flight Manu...

Page 182: ... consists of a fuel tank selector switch tubing electrical wiring and hardware necessary to complete the installation The provisions portion of the kit comprise those items which are not readily removableonce installed The equipment portion of the kit consists primarily of the tank filler connection drain transfer lines and attaching hardware The fuel tank mounts in the forward portion of the bagg...

Page 183: ...center pedestal has a three position switch labeled AUTO OFF and ORIDE override In the OFF position the interconnect valve is powered to the closed position In the ORIDE position the valve is powered to the open position In the AUTO position the IIDS determines when 190 liters 50 U S Gallons have been used from the main tanks and automatically opens the interconnect valve to transfer the fuel When...

Page 184: ... CAUTION light Each windshield consists of an outer layer of tempered glass a middle layer of PPG 112 plastic and an inner layer of acrylic plastic plexiglass with embedded electrical heating elements The heated portion is confined to that area at the average pilots optimum eye level and is approximately 18 centimeters 7 inches in height extending from the windshield centerpost to either crew door...

Page 185: ... forward into the outboard portion of each wing The nose wheel is enclosed within doors when in the retracted position The main wheels are equipped with an independent hydraulic braking system actuated by pedals mounted on the pilots anti torque pedals Each wheel has an independent shock strut downlock mechanism and a hydraulic actuator cylinder The wheel configuration 230 s wings are divided into...

Page 186: ...he weight of the helicopter is on the wheels The Landing Gear Control Panel is located on the instrument panel and contains the LDG GEAR switch UNSAFE light three gear condition lights L N R TEST switch and AUDIO MUTE switch The three condition lights illuminate green when all three wheels are fully extended and the downlock plungers are positioned properly The UNSAFE light illuminates when the la...

Page 187: ... If PC2 should fail the wheels may be extended by the EMER PULL GEAR handle located on the right front of the pedestal When the handle is pulled hydraulic pressure to the retract side of the cylinders is relieved which allows gravity air loads and spring pressure nose gear only to force the landing gear to the extended position The spring loaded downlock plungers lock the gear into position Differ...

Page 188: ... The mute function is reset when airspeed increases above 55 knots or if EMER BUS 2 power is lost The AUX SYS PITOT STATIC control switches are located on the instrument panel and provide isolation disabling of the warning horn pressure differential switch in the event of a malfunction of the primary pitot static system associated plumbing Operational procedures for the Retractable Landing Gear co...

Page 189: ...ot Brakes Kit provides differential braking control of the wheel landing gear at the copilot station when the Dual Control Kit is installed The copilot brakes operate in exactly the same manner as the pilots They consist of a set of hydraulic cylinders mounted to the copilot directional control pedals and the plumbing necessary to connect to the braking system hydraulic lines The weight increase w...

Page 190: ...errain is rough or when camera pods FLIR NightSun or other external equipment require increased ground clearance The High Skid Gear Kit consists of the a replacement skid gear assembly and fuselage mounted steps for the crew 2 x J steps and passenger doors 2 x U steps A small platform step is also mounted to each skid tube just below the passenger door steps The High Skids may be interchanged with...

Page 191: ... paths of emergency egress from the helicopter the standard cabin door windows are also emergency exits The entire transparency of each unit is designed to POP OUT from inside or outside the cabin Each unit is securley mounted in synthetic rubber channel and requires a two step process for manual activation This kit is recommended when conducting frequent overwater operations and when the high den...

Page 192: ...eight above the GROUND from 0 to 2000 feet The Radar Altimeter EFIS is included for IFR configurations equipped withhKFC 500 and FLIGHT DIRECTOR The King KRA 405B system includes the remote mounted transmitter receiver unit two KA 54 antennas and the KNI 416 indicator The instrument features a red OFF flag a TEST button a decision height DH adjust knob a DH indicator light white and a indicator ne...

Page 193: ...formation including Airport Data Communication Frequencies Navaid Data Airspace Information ARTCC Information and Minimum Safe Altitudes The installation consists of the panel mounted unit a database cartridge an altitude input and a KA 91 antenna Additional components may be added to increase the KLN 90 s capabilities Some of the optional interfaces include an external course deviation indicator ...

Page 194: ...uency The Pointer 4000 is specifically designed for helicopter use It activates at 6 G loads 360 in azimuth as well as full vertical components Mounted inside the baggage compartment the ELT is a completely self contained battery powered unit with antenna connections which attach to an external fuselage mounted antenna The ELT has a switch for manual operation and testing The battery has a three y...

Page 195: ...uter Air Data System a Variable Vne Airspeed Indicator and the wiring and equipment necessary to complete the installation When the kit is installed the Vne Computer continuously calculates the Vne for ambient conditions and drives the barber pole needle to that value When the airspeed needle reaches the same point as the barber pole the warning audio is activated to alert the pilot to impending e...

Page 196: ...E All Flight Director configurations require EFIS and Radar Altimeter The number of crew members and systems equipment requirements for IFR flight are governed by aircraft seating capacity the type of operation i e Part 135 Air Taxi Charter Part 91 General Aviation Corporate Private and in some cases impose the addition of specific equipment i e Cockpit Voice Recorder Flight Data Recorders and Eme...

Page 197: ...roMech 26 6 12 1 KTR 908 VHF Comm 2 6 0 2 7 KNR 634A NAV 1 ElectroMech 10 8 4 9 KNR 634A NAV 2 ElectroMech 6 8 3 1 KDF 806 ADF Wheel 8 2 3 7 KDM 706 DME ElectroMech 7 2 3 3 Transponder Mode S 12 4 5 6 Gyro ElectroMech 12 1 5 5 Installed Weight Wheel Gear 245 3 111 3 KDF 806 ADF Wheel Remove 8 2 3 7 ADF KDF 806 Skid Add 9 5 4 3 Installed Weight Skid Gear 246 6 111 9 Notes Customer responsible for o...

Page 198: ...FIS 24 0 10 9 KTR 908 VHF Comm 2 6 0 2 7 KNR 634A NAV 1 EFIS 10 0 4 5 KNR 634A NAV 2 EFIS 6 8 3 1 KDF 806 ADF Wheel 8 2 3 7 KDM 706 DME EFIS 6 3 2 9 Transponder Mode S Flight Director 11 6 5 3 Rad Alt KRA 405 EFIS 12 6 5 7 Gyro 4 EFIS 14 9 6 8 Installed Weight Wheel Gear 320 5 145 4 KDF 806 ADF Wheel Remove 8 2 3 7 ADF KDF 806 Skid Add 9 5 4 3 Installed Weight Skid Gear 321 8 146 0 Notes Customer ...

Page 199: ... 10 9 KTR 908 VHF Comm 2 6 0 2 7 KNR 634A NAV 1 EFIS 10 0 4 5 KNR 634A NAV 2 EFIS 6 8 3 1 KDF 806 ADF Wheel 8 2 3 7 KDM 706 DME EFIS 6 3 2 9 Transponder Mode S Flight Director 12 8 5 8 Rad Alt KRA 405 EFIS 12 6 5 7 Gyro 4 EFIS 14 9 6 8 Installed Weight Wheel Gear 344 6 156 3 KDF 806 ADF Wheel Remove 8 2 3 7 ADF KDF 806 Skid Add 9 5 4 3 Installed Weight Skid Gear 345 9 156 9 Notes Customer responsi...

Page 200: ...ontal Situation Indicator EHSI These AMLCD indicators are configured as one EHSI and one EADI or two EHISs and two EADIs They display aircraft heading and attitude along with navigational and AFCS information The EADI and EHSI have the same bezel configuration Each bezel is split in two sections a vertical section and a horizontal section The bezel vertical section contains four softkeys C and and...

Page 201: ...s Each EFIS unit allows for ARINC 429 LNV source inputs from two LNV systems The AFCS interfaces with EFIS through an ARINC 429 communication bus The EFIS provides the AFCS with selected course or desired track selected heading magnetic variation radio altitude lateral deviation DME distance pitch attitude roll attitude and equipment ID The AFCS provides the EFIS with course ref selected heading a...

Page 202: ...on and attitude display on only one of the units Each EFS 40 display normally operates individually as an Electronic Attitude Director Indicator EADI or an Electronic Horizontal Situation Indicator EHSI The EADI display modes include normal APPROACH and ENROUTE Composite APPROACH and ENROUTE and Test Maintenance and System Configuration It also displays Turn Rate and incorporates an inclinometer o...

Page 203: ...mponents and architecture are shown in the block diagram below Detailed system description and operational information may be found in the attached document link KFC500PG single PDF DUAL PILOT IFR with BASIC SCAS ATT with E M Instruments No Flight Director System Components KFC 500 Flight Controls KCP 520 Flight Computer KLA 575 Linear Actuators KSA 572 Trim Actuators KRG 333 Accelerometer Rate Gy...

Page 204: ...ude Indicator and HSI with four four inch EFS 40 displays and then adds the KFC 500 Flight Control System System components and architecture are shown in the block diagram below Detailed system description and operational information may be found in the attached document link KFC500PG single PDF DUAL PILOT IFR with Single AFCS KFC500 EFS 40 FOUR TUBE with Flight Director System Components KFC 500 ...

Page 205: ... Pitch Roll and Yaw SCAS Engage on ground Autopilot engage above 50 knots Modes HDG NAV APR ALT HOLD SELECT VS IAS VNAV The Single Dual Pilot IFR with Dual AFCS KFC500 configuration consists of a two completely integrated digital three axis pitch roll and yaw dual electronic channel flight control systems with yaw damper coupled Flight Director System 1 only and a four tube Electronic Flight Instr...

Page 206: ...tion in it s standard configuration Instruments for a second pilot may be added to the left side of the instrument panel by the addition of the Copilot Instrument Kit When EFIS is installed the Atitude Indicator and directional Gyro are replaced by the Electronic displays This kit is required when the dual control kit is installed The kit consists of the following principal items Airspeed Indicato...

Page 207: ...BLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 STANDBY ATTITUDE INDICATOR The Standby Attitude Indicator is a backup attitude indicator with a self contained electrically isolated DC electric powered gyro This three inch instrument is required by FAA regulation for Instrument Flight Rules IFR operations ...

Page 208: ...l stick a collective control lever with twist grip dual throttle control and anti torque pedals and interconnecting linkages Similar to the pilots controls in appearance they provide all the major functions as well as identical control feel Provisions are incorporated in all Bell 430 airframes to accept the dual control kit and they may be added or removed as required If the dual controls are inst...

Page 209: ...ENTATIVE PRODUCT DATA JANUARY 2003 COPILOT INTERCOM SYSTEM The Copilot Intercom System provides the copilot or forward passenger the same radio transmit and receive functions as the pilot as well as the same radio monitoring capability The King KMA 24H 71 control panel mounts on the lower edge of the instrument panel The Copilot ICS is required when Dual Controls are installed ...

Page 210: ...struments and displays The benefits of a complete provision kit are future flexibility in installation or removal of some avionics without extensive modifications to the existing configuration minimum electromagnetic compatibility interference and optimum antenna location energy radiation pattern reception The provisions include all wiring connectors and mounting provisions space and dedicated fas...

Page 211: ...HF AM communications transceiver No 2 King KTR 908 is a lightweight airborne radio providing two way amplitude modulated communications within the frequency range of 118 0 to 135 975 MHz The kit consists of the remote mounted transceiver unit mounting rack the control panel and the antenna The second control panel is mounted at the top of the instrument panel Internal audio leveling provides const...

Page 212: ... and provides data to the glideslope indicator of the HSI The system senses marker beacons providing both visual and audio signals to indicate station passage The kit consists of the remote mounted receiver unit the control panel the marker beacon control the mounting rack and three antennas The main control panel mounts at the top of the instrument panel NO 1 NAV ILS MARKER BEACON RECEIVER NO 2 N...

Page 213: ...06 supplies magnetic bearing information on the tuned station to the bearing pointer of the HSI It also provides ADF audio to the Intercommunication System ICS headset when the ADF switch is in the ON position The kit consists of the remote mounted receiver the control panel the mounting rack a combined loop and sensing antenna The control panel is located at the top of the instrument panel The an...

Page 214: ...nge to station in nautical miles the course rate ground speed along a direct bearing to station in knots and the time to station in minutes for VOR DME navigation transmitters The kit consists of the remote mounted receiver transmitter unit the mounting rack the display panel KDI 572 and the antenna For non EFIS configuration the display panel is located on the instrument panel below the HSI and c...

Page 215: ...e with the FAA Traffic Alert and Collision Avoidance System TCAS II and future compatibility with ATCRBS Mode S ground stations FAA regulations require that transponders installed in U S registered aircraft with ten or more seats and which are engaged in sometypes of Air Transport Operations must be MODE S compatible Each Mode S transponder installation is assigned a unique address code consisting...

Page 216: ...leed air tubing and hoses purge switches and other hardwarerequired to complete the installation The separators are installed within the left and right air induction cowlings and cause no aerodynamic change to the helicopter Each of the 530 filter elements tube assemblies in each of the separators through which all inlet air must pass consists of a vortex generator bonded into an inlet tube and a ...

Page 217: ...face of the separator However the numerous filter elements are placed so that there will be sufficient air flow by passing the blocked elements for flight to be continued The purge action of the bleed air venturis may be turned off when additional engine power is required A purge switch for each engine is located in the overhead console When purge is off the separators continue to direct particles...

Page 218: ...sions in the airframe and passenger doors for air ducts and outlets The engine bleed air powered heating cooling unit is located beneath a removable panel in the baggage compartment floor System operation is controlled by overhead console switches Two separate air distribution systems provide conditioned de humidified air to the cabin The COOL air system is located in the cabin roof and feeds into...

Page 219: ... of operation and sets the desired cabin temperature The DISTR SYS distribution system button controls the diverter valves which direct air to the upper or lower outlets The PASS DOOR OUTLETS button is selected when maximum defogging is required The ECU FLOW button acts to provide either the maximum NORM or a reduced ECON bleed air supply from the engines The ECON position may be selected after th...

Page 220: ...g snow The kit consists of a deflector shell for each engine air inlet Provisions for installation of the baffles are part of the standard configuration and are located on the transmission fairing in front of each air inlet Operating procedures are found in the FAA approved Flight Manual Supplement BHT 430 FMS 20 The baffles are approved for operation at temperatures up to 20 C 68 F above which th...

Page 221: ...m which is built into the fuselage bulkhead just forward of the right hand pas senger cabin door In the event of a water landing there are three separate means of activating the deployment system Activating handles are located in the cockpit aft of the overhead con sole the passenger cabin above the raft and on the R H forward exterior fuselage Each handle is protected by a transparent break away ...

Page 222: ...t 122 centimeters high The optional hinged panel Litter door kit consists of an additional panel door on the left hand forward side of the cabin The standard main door is attached with a hinge to the panel door in a manner similar to the Bell LongRanger series This panel door also is hinged and both doors can swing open to give a 54 inch 137 centimeter access to the cabin to facilitate litter or b...

Page 223: ... LANDING LIGHT NO 430 706 002 XXX The second landing light is a single high intensity 450 watt wide beam retractable light located in the lower part of the fuselage The ON OFF STOW power switch is located on the pilots collective control box The second landing light kit is required for the conduct of night category A operations The Weight increase with the second landing light kit installed is 1 9...

Page 224: ...ls located on the cyclic instrument panel center pedestal and overhead console are edgelit and consist of a three position HOIST PWR I OFF I RESET switch a HOIST power annunciator a CABLE CUT ARM OFF switch a C C ARM caution annunciator and a guarded HOIST CABLE CUT switch connected to MK44 MOD 0 explosive cartridge for emergency cable release Pilot HOIST CTL switch is located on top of the cyclic...

Page 225: ...have any duty cycle down up operations limitations It is the responsibility of the aircraft operator to seek and receive approval from the appropriate regulatory agency to conduct Class D Rotorcraft Load operations Human External Load The weight increase with the provisions only installed is 12 9 kilograms 28 4 pounds The weight increase for thehoist equipment installed is 68 9 kilograms 152 0 pou...

Page 226: ...limit combination of rotorcraft and load of 4218 kilograms 9300 pounds The Cargo Hook Kit consists of the provisions structural electrical and mechanical release and the removable equipment cargo hook and suspension assembly The provisions which may be ordered alone for future use are comprised of two suspension fittings on the belly near the center of gravity electrical release switch arming swit...

Page 227: ...of a failure of the electrical release switch The suspension assembly is quickly detachable if desired however operation of the helicopter with no load on the cargo hook is authorized understandard airworthiness certificate for both VFR and IFR conditions without removing the unit from the helicopter When there is no load attached to the cargo hook an elastic bungee cord retainer prevents the pivo...

Page 228: ...communication wires and cables The WSPS is designed to reduce the possibility of wires entering the cockpit area damage to the flight controls during a wire strike or of wires becoming entangled in the landing gear In actual cases this system has proven effective against multiple wire strikes The WSPS consists of an upper cutter deflector a windshield deflector and two lower cutter deflectors Each...

Page 229: ...d the CVR continuously records on three separate channels the last 30 minutes of audio input from the pilot s intercommunication system ICS the copilot s ICS if installed and a cockpit area microphone The Loral A100 CVR consists of a recorder unit CVR control test panel with integral area microphone impact switch and the racks and mounts required for installation In operation the system shuts down...

Page 230: ...ats for three passengers each 6 passengers total in the main cabin which face each other in the traditional club car arrangment The first row passenger seats aft facing include padded head rests The aft row passenger seats feature fold down backs to provide easy access to the baggage compartment The seating is available in four standard fabric color coordinated styles DARK RED BLUE BROWN or GRAY A...

Page 231: ...rs total in the main cabin which face each other in the traditional club car configuration The first row of two individual passenger seats aft facing include padded head rests and the space between them is suitable for installation of a refreshment entertainment system console The aft row of three passenger seats feature fold down backs for access to the baggage compartment The seating is availabl...

Page 232: ...ngers each 6 passengers total which face each other in the traditional club car arrangment The first row passenger seats aft facing include padded head rests and the center seat back folds down to form a tray with receptacles for refreshments The aft row passenger seats feature fold down backs for access to the baggage compartment The seating is available in any of eight fabric and leather color c...

Page 233: ...nd inertia reel arranged with two rows of two and one row of three forward facing seats in the main cabin The two forward rows two seats each may be specified with either folding or non folding seatbacks The aft row passenger seats feature fold down backs to provide easy access to the baggage compartment The seating is available in four standard fabric color coordinated styles DARK RED BLUE BROWN ...

Page 234: ...o rows of three forward facing seats in the main cabin The two forward rows have folding seatbacks The middle row outboard seats have fold forward seat bottoms to provide easy entry to the aft row of seats The aft row passenger seats feature fold down backs to provide easy access to the baggage compartment When this seating configuration is used for overwater operations the Emergency Aft Passenger...

Page 235: ...irst row passenger seats aft facing include padded head rests The middle row has folding seatbacks and the middle row outboard seats have fold forward seat bottoms to provide easy entry to the aft row of seats The aft row passenger seats feature fold down backs to provide easy access to the baggage compartment When this seating configuration is used for overwater operations the Emergency Aft Passe...

Page 236: ...g composite foam lead foil and vinyl covered fiberglass batting Access panels and bulkhead passages for wiring ducting and plumbing are sealed to eliminate extraneous sound paths The Standard Soundproofing Kit is ONLY compatible with the Standard UTILITY Interior Trim A complete instalation requires the XXX Kit plus either the XXY or XXZ kit depending on installation of the Aux Fuel Kit The Standa...

Page 237: ...mrests are covered with color coordinated leather Inset into the face of each armrest is an accent trim of fine hardwood Lower sidewall panels are also leather covered with carpet inserts near the floor Upper sidewall panels window surrounds are in an off white color The floor covering is a tightly woven wool carpet The headliner is covered with off white synthetic leather Seat belts are color coo...

Page 238: ...d from alternating layers of sound attenuating composite foam lead foil and vinyl covered fiberglass batting Access panels and bulkhead passages for wiring ducting and plumbing are sealed to eliminate extraneous sound paths The Corporate Soundproofing Kit is ONLY compatible with the CORPORATE Interior Trim and is required when the CORPORATE Trim is specified A complete instalation requires the XXX...

Page 239: ... PRODUCT DATA JANUARY 2003 HIGH VISIBILITY MAIN ROTOR BLADES No 430 015 001 XXX The High Visibility Main Rotor Blade Paint Option provides increased safety when operating in congested airspace The upper surface of the main rotor blades is painted in alternating bands of White and International Orange There is no increase in empty weight when this option is chosen ORANGE WHITE MARKINGS ...

Page 240: ...l effectiveness of your 430 to include Sliding Passenger Doors Weather and Search Radars Moving Map Displays Flight Management Systems TCAS equipment Electronic Flight Publications Database Printer and Airborne Radio Telephone and Satellite Communications Systems Bell s FAA Approvedcustomized installations are engineered integrated and tested to the same standards FAR 27 and FAR 29 as the basic he...

Page 241: ...E BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 SPECIAL TRIM PACKAGES PRECIOUS METAL PLATING FOR FITTINGS SLIDING PASSENGER CABIN DOOR LH SPECTROLAB SX 5 STARBURST SEARCHLIGHT ...

Page 242: ...T CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 RETRACTABLE PASSENGER STEPS SPECIAL PURPOSE WINDOWS EXP 3 PANEL CAMERA WINDOW HOSPITAL BASED EMS INTERIOR SYSTEMS ELECTRONIC NEWS LAW ENFORCMENT SENSOR SUITES WITH DATA DOWNLINK ...

Page 243: ...1117 MT PLEASANT AIRPORT MT PLEASANT PA 15666 VOICE 724 887 4413 FAX 724 887 3977 WEB SITE has corp com VICE PRESIDENT NEW BUSINESS DEVELOPMENT CHUCK HALLET chuck has corp com HELI DYNE SYSTEMS INC AN AFFILIATE OF CORPORATE JETS INC 9000 TRINITY BLVD HURST TX 76053 817 282 9804 FAX 817 282 8329 GENERAL MANAGER J M MULLINS jmmullins heli dyne com MARKETING M MCCURLEY mmccurley heli dyne com EDWARDS...

Page 244: ...HIS IS AN UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ...

Page 245: ...T THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 SECTION THREE DIMENSIONS DESIGN SPECIFICATIONS AND WEIGHTS ...

Page 246: ...HIS IS AN UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 ...

Page 247: ...E PRODUCT DATA JANUARY 2003 CONTENTS EXTERNAL DIMENSIONS SKID GEAR 246 RETRACTABLE WHEELS 247 HELIPORT LOADING DATA 248 INTERIOR DIMENSIONS 249 DOOR DIMENSIONS 250 INTERNAL VOLUMES 251 430 STATION DIAGRAMS SKID GEAR 252 RETRACTABLE WHEELS 254 DESIGN SPECIFICATIONS 256 WEIGHTS TABULAR PERFORMANCE SKID GEAR 258 RETRACTABLE WHEELS 260 OPTIONAL EQUIPMENT WEIGHTS 262 IFR CONFIGURATIONS 264 ...

Page 248: ...ELS AND DOOR LIP WHEN CONSIDERING HANGAR DOOR WIDTH AND HEIGHT 30 9 FEET 9 4 METERS DIMENSIONS ARE APPROXIMATE DIMENSIONS ARE ROUNDED TO THE NEXT HIGHEST TENTH FOOT METER ENGLISH METRIC OVERALL HEIGHT STANDARD SKIDS 13 2 FT 4 0 M HIGH SKIDS 14 2 FT 4 3 M OVERALL LENGTH FUSELAGE 44 1 FT 13 5 M ROTOR TURNING 50 2 FT 15 3 M ROTOR IN X 44 6 FT 13 6 M MAXIMUM WIDTH FUSELAGE 11 3 FT 3 5 M ROTOR TURNING ...

Page 249: ...TE DIMENSIONS ARE ROUNDED TO THE NEXT HIGHEST TENTH FOOT METER ENGLISH METRIC OVERALL HEIGHT 12 2 FT 3 7 M OVERALL LENGTH FUSELAGE 44 1 FT 13 5 M ROTOR TURNING 50 2 FT 15 3 M ROTOR IN X 44 6 M 13 6 M MAXIMUM WIDTH FUSELAGE 11 3 FT 3 5 M ROTOR TURNING 42 0 FT 12 8 M ROTOR IN X 30 9 FT 9 4 M MAIN ROTOR DIAMETER 42 0 FT 12 8 M MAIN ROTOR CHORD 14 2 IN 0 361 M NUMBER OF BLADES 4 4 TAIL ROTOR DIAMETER ...

Page 250: ...IAMETER 8 INCHES 203 MILIMETERS LENGTH 100 INCHES 2 54 METERS CONTACT AREA D 2 X 1 L 24 SQ INCHES 155 SQ CENTIMETERS 101 INCHES 2 57 METERS SKID LANDING GEAR STATIC LOADING MAX GROSS WEIGHT LOADING CONTACT AREA CONTACT PRESSURE 9000 LB 4082 KG FORWARD AFT FORWARD AFT FORWARD AFT ENGLISH 2688 LBS 6312 LBS 48 SQ INCHES 48 SQ INCHES 56 PSI 132 PSI METRIC 1219 KG 2863 KG 310 SQ CM 310 SQ CM 3 94 KG SQ...

Page 251: ...UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 INTERIOR DIMENSIONS ...

Page 252: ...N UNCONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 DOOR DIMENSIONS ...

Page 253: ...INTERNAL VOLUMES CABIN SEAT TO ROOF CREW COMPARTMENT NOSE CABIN SEAT TO FLOOR PARCEL SHELF CABIN FLOOR LOAD LIMIT CABIN LOAD LIMIT STRUCTURAL BAGGAGE COMPARTMENT COMPARTMENT LOAD LIMIT COMPARTMENT FLOOR LOAD LIMIT AFT AVIONICS COMPARTMENT 1 05M3 37 2FT3 226 80KG 500 0LB 488 2KG M2 100LB FT2 0 10M3 3 7FT3 0 17M3 6 0FT3 0 6 M3 19 FT3 488 20KG M2 100LB FT2 3 9 M3 139 FT3 1252 KG 2760LB 1 87M3 65 9FT3...

Page 254: ...ONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 STATION DIAGRAM SKID GEAR ...

Page 255: ...ONTROLLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 STATION DIAGRAM SKID GEAR ...

Page 256: ...LLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 STATION DIAGRAM RETRACTABLE WHEELS ...

Page 257: ...LLED DOCUMENT THIS ELECTRONIC DOCUMENT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 STATION DIAGRAM RETRACTABLE WHEELS ...

Page 258: ...48 348 TAIL ROTOR Number of Blades 2 2 Diameter 2 1 meters 6 9 feet Chord 25 4 centimeters 10 inches RPM 100 1881 1881 ENGINES TWO ROLLS ROYCE 250 C40B Engine Rated Shaft Horsepower Twin Engine Power Each 5 Minute 557 kW 747 SHP Maximum Continuous 461 kW 618 SHP Single Engine Power 30 Second 629 kW 844 SHP 2 Minute 605 kW 811 SHP 30 Minute 588 kW 789 SHP TRANSMISSION RATINGS 100 RPM 5 Minute Main ...

Page 259: ...NAL Empty Weight note 1 2430 5358 Useful Load 1788 3942 Maximum Gross Weight 4218 9300 Internal EXTERNAL LIFT Maximum Gross Weight 4218 9300 Maximum External Load 1270 2800 NOTE 1 The empty weight includes thirty five pounds of engine oil Ballast is not included in the standard configuration weight ballast is a function of installed equipment METRIC ENGLISH SEATING Crew 1 1 Passengers 8 9 8 9 FUEL...

Page 260: ...ous OEI ISA ft 13 590 11 840 10 190 8630 7740 Cruise Sea Level ISA Maximum Continuous Speed ktas 143 142 141 140 139 Long Range Cruise Speed average ktas 130 130 131 131 131 Range at LRC No Reserve nm 367 364 360 355 353 Category A Takeoff and Landing Ceiling Note 2 Ground Level or Elevated Helipad ISA ft 8000 6000 3600 1200 Note 2 ISA 20C ft 5300 3100 900 8730 lbs Note2 SL Endurance Loiter 65 kts...

Page 261: ...s OEI ISA m 4142 3609 3106 2630 2359 Cruise Sea Level ISA Maximum Continuous Speed km h 265 263 261 259 258 Long Range Cruise Speed average km h 241 241 243 243 243 Range at LRC No Reserve km 680 675 667 658 654 Category A Takeoff and Landing Ceiling Note 2 Ground Level or Elevated Helipad ISA m 2438 1829 1097 366 Note 2 ISA 20C m 1615 945 274 3960 Kg Note 2 SL Endurance Loiter 120 km h ISA hr 3 8...

Page 262: ... OEI ISA ft 13 590 11 840 10 190 8630 7740 Cruise Sea Level ISA Maximum Continuous Speed ktas 147 146 145 144 143 Long Range Cruise Speed average ktas 133 134 134 135 135 Range at LRC No Reserve nm 286 283 280 277 275 Category A Takeoff and Landing Ceiling Note 2 Ground Level or Elevated Helipad ISA ft 8000 6000 3600 1200 Note 2 ISA 20C ft 5300 3100 900 8730 lbs Note 2 SL Endurance Loiter 65 kts I...

Page 263: ...s OEI ISA m 4142 3609 3106 2630 2359 Cruise Sea Level ISA Maximum Continuous Speed km h 272 271 269 267 265 Long Range Cruise Speed average km h 246 248 248 250 250 Range at LRC No Reserve km 530 524 519 513 510 Category A Takeoff and Landing Ceiling Note 2 Ground Level or Elevated Helipad ISA m 2438 1829 1097 366 Note 2 ISA 20C m 1615 945 274 3960 Kg Note 2 SL Endurance Loiter 120 km h ISA hr 2 8...

Page 264: ...OINTER 4000 4 8 2 2 430 706 004 103 VNE COMPUTER ASSOCIATED HORN 10 1 4 6 4 ENGINE 230 706 501 107 PARTICLE SEPARATOR 28 0 12 7 1 ENVIRONMENT 222 706 018 119 ENVIRONMENTAL CONTROL SYSTEM 98 5 44 7 EQUIPMENT 222 706 014 103 CO PILOT WHEEL BRAKES 4 3 2 0 430 706 905 103 CARGO HOOK PROVISIONS 2 9 1 3 222 706 904 107 CARGO HOOK EQUIPMENT 2800 LBS CAP 38 1 17 3 230 706 502 115 SNOW BAFFLES 3 8 1 7 430 ...

Page 265: ...ndard blades is required to incorporate this feature 1 Price and or Weight includes credit for basic ship hardware removed 90 8 kg 4 VNE Computer Horn is REQUIRED for ALL Category A Operations The Second Landing Light is REQUIRED for ANY NIGHT Category A Operation Additional Cat A equipment and crew requirements are specified in the Instrument Flight Rules AFCS Configurations Pages immediately fol...

Page 266: ...tube EFIS Dual AFCS KFC 500 w Flight Director Equipment included in each configuration and installed weights may be found in the Tables located on the following pages Category A Operations requires the addition of the OPTIONAL Category A VNE Computer Warning Audio NIGHT Category A Operations reguires the addition of the OPTIONAL Second Landing Light Additional IFR configurations or available as cu...

Page 267: ...I ICE ADVISORY 63 ANTI ICING SYSTEM 89 ANTI ICING FUEL ADDITIVE 93 ANTI TORQUE 32 36 ANTI TORQUE SYSTEM 146 ANTICOLLISION LIGHT 159 ANTICOLLISION LIGHTS 77 APPROACH PLATE HOLDER 27 ARINC 429 DA TA BUS 108 ASH TRAYS 26 29 ATTITUDE INDICA TOR 44 AUTOMATIC DIRECTION FINDER 213 AUTOMA TIC ENGINE LOAD SHARING SYSTEM 108 AUTOMA TIC START 105 AUTOMATIC START SEQUENCE 47 AUTORELIGHT 105 AUTOROTATION 126 1...

Page 268: ... ROTOR BLADE 141 COMPOSITE PAGE 57 COMPOSITE YOKE 139 COMPRESSOR MODULE 85 COMPRESSOR INLET AIR TEMPERATURE SENSOR T1 109 COMPRESSOR WASH 89 CONDENSATION DRAINS 41 CONSTRUCTION FEATURES 153 CONTINUOUS COMBUSTION 86 CONTINUOUS FUNCTIONAL CHECK 106 COPILOT BRAKES 189 COPILOT INSTRUMENTS 206 COPILOT INTERCOM SYSTEM 209 CORPORATE INTERIOR TRIM 237 CORPORATE INTERIOR 16 CORPORATE SOUNDPROOFING 238 CORR...

Page 269: ...16 ENGINE ACCESSORIES 99 ENGINE COMPARTMENTS 110 ENGINE CONDITION MONITORING 107 ENGINE CONTROL 101 ENGINE CONTROL SYSTEM 101 ENGINE COOLING 94 ENGINE DECK 110 ENGINE FAULT ANNUNCIATORS 108 ENGINE FIRE 48 ENGINE FIRE DETECTION 112 ENGINE FIRE BOTTLE 113 ENGINE FUEL PUMP 109 ENGINE HISTORY 59 ENGINE HOURMETER 59 ENGINE MOUNTED ACCESSORIES 109 ENGINE MOUNTED FUEL FILTER 109 ENGINE OIL SYSTEM SCHEMAT...

Page 270: ...NTITY 55 FUEL REQUIREMENTS 93 FUEL SHUTOFF VALVE 122 FUEL SYSTEM FILLER PORT 123 FUEL SYSTEM SWITCHES 122 FUEL TANK INTERCONNECT 124 FUEL TEMPERATURE 58 FUEL VALVE 69 FULL AUTHORITY DIGIT AL ELECTRONIC CONTROL 101 FULL PERIMETER SEALING 22 FUNCTION KEYS 50 FUSELAGE ASSEMBLY 153 FUZZ BURNER 10 120 FWD LATERAL RESTRAINTS 129 G GAS GENERA TOR NG GOVERNOR 104 GAS PRODUCER GEARING 91 GAS PRODUCER SUPPO...

Page 271: ...JET B JP 4 93 K KEYED LOCK 22 155 KICK IN STEP 155 KING GOLD CROWN III PROVISIONS 210 KING KDF 806 213 KING KDM 706 214 KING KNR 634 212 KING KTR 908 211 KING MST 67A 215 L LABEL 52 LANDING GEAR 162 LANDING SEARCH LIGHT 35 77 LARGE DOORS 22 LCD 49 LDG GR UP 68 LEADING EDGE SLAT 159 LEADING EDGE STRIP 139 LEVELING 171 LEVELING PLATE 171 LIFTING 171 LIGHTING 77 LIQUID CRYST AL DISPLAY 49 LIQUID INER...

Page 272: ...CESSORIES 262 OPTIONAL EQUIPMENT CONTENTS 177 OUTSIDE AIR TEMPERA TURE INDICATOR 54 OVER TEMPERA TURE SENSOR 70 OVERHEAD CONSOLE 76 OVERSPEED 70 OVERSPEED PANEL 48 OVERSPEED FUNCTIONAL TEST 107 OVERTEMPERATURE INDICA TORS 125 OVERTORQUE 34 P PANELS 167 PARKING AND MOORING 169 PARKING BRAKE 70 PARTICLE SEPARA TOR 216 PASSENGER CARGO COMPARTMENT 28 PC 1 37 PC 2 37 PEDAL LENGTH ADJUSTMENT 36 PERMANEN...

Page 273: ... 34 SHEAR RESTRAINTS 144 SHOE ASSEMBLY 163 SHOULDER HARNESS 15 24 SIDE STEP 155 SINGLE ENGINE FLIGHT 126 SINGLE FILLER PORT 123 SINGLE PILOT DUAL PILOT IFR WITH DUAL AFCS KFC50 205 SINGLE PILOT OPERATION 14 SKID LANDING GEAR 11 155 162 SKID TUBES 163 SKY LIGHTS 23 154 SNOW BAFFLE PROVISIONS 114 SNOW BAFFLES 220 SOLID STATE INVERTER 75 SOUNDPROOFING 21 SPACIOUS CABIN 8 SPARE DRIVE PADS 92 SPECIFICA...

Page 274: ...MISSION SCHEMA TIC 128 TRANSMISSION ENGINE COWLINGS 160 TRANSMISSION COWLING 160 TRANSMISSION ISOLATION MOUNT 129 TRANSMISSION LIFT LINK 130 TRANSMISSION OIL LINES 111 TRANSMISSION OIL SCHEMATIC 134 TRANSMISSION OIL TEMPERATURE AND PRESSURE 54 TRANSMISSION POWER RATING 130 TRANSPONDER MODE S 215 TRANSPORT CATEGORY ROTORCRAFT 14 TRIM TABS 141 TRIPLE TACHOMETER 53 TRIPLE TORQUE DISPLA Y 53 TRUNNION ...

Page 275: ...NT MAY HAVE BEEN SUPERCEDED THE MOST CURRENT DOCUMENT INFORMATION IS AVAILABLE FROM YOUR BELL HELICOPTER TEXTRON REPRESENTATIVE PRODUCT DATA JANUARY 2003 WINGTIP FLOAT PACKED 181 WIRE STRIKE PROTECTION SYSTEM 228 WORK PLATFORMS 155 164 X XMSN CHP 64 XMSN OIL 62 ...

Page 276: ...ER TEXTRON DIVISION OF TEXTRON CANADA LTD 12 800 rue de l Avenir Mirabel Quebec Canada J7J1R4 Phone 450 437 2729 Fax 450 437 2066 The data set forth in this brochure are general in nature and may vary with conditions For performance data and operating limitations for any specific flight mission reference must be made to the approved flight manual Written Edited Layout by 2003 Bell Helicopter Textr...

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