BELL HELICOPTER 430 Maintenance Manual Download

Page: 170 / 186

BHT-430-MM-2

5-00-00
Page 140

Rev. 15 26 JAN 2007

NOTE

If FADEC faults are recorded and engine was
operated above 109.6% engine torque, OEI
overtorque has occurred. Refer to following

step 2

If the ECU did not record any FADEC faults, indicating a

properly functioning ECU, and provided the 2 minutes and/or
the 30 seconds limits are not exceeded, no maintenance is
required on the helicopter drivetrain system. Clear OEI
maintenance advisory light using MT35 program.

Rolls-Royce
250-C40B Operation
and Maintenance
Manual, Publication
CSP 21000

Perform engine overtorque inspection as required.

BHT-430-FM-1

NOTE

An OEI overtorque is an incident where engine
torque is greater than the allowed limits as follows:

Operation at 98% to 105.3% engine torque for period
greater than 2 minutes continuous.

Operation at or above 105.3% engine torque for
period greater than 30 seconds continuous.

Operation above 109.6% engine torque with FADEC
in Manual MODE, Degraded MODE or Failed Fixed
MODE.

Operation above 109.6% for period longer than 16
seconds.

When an OEI overtorque occurs, do the steps that follow:

Chapter 95

Verify the maintenance pages of both IIDS screens for

any exceedances. Review ECU engine faults, engine
exceedances and engine history data pages.

CONDITIONAL INSPECTIONS

5-49.

ONE ENGINE INOPERATIVE (OEI) (CONT)

DATA REFERENCE

INSPECTION TASK DESCRIPTION

INITIAL

MECH OTHER

Summary of Contents for 430

Page 1: ... Bell Helicopter Textron Inc and Airworthiness Directives AD issued by the applicable regulatory agencies shall be strictly followed REISSUE 30 JUNE 1999 REVISION 19 1 NOVEMBER 2012 COPYRIGHT NOTICE COPYRIGHT 2012 BELL HELICOPTER TEXTRON INC AND BELL HELICOPTER TEXTRON CANADA LTD ALL RIGHTS RESERVED MAINTENANCE MANUAL VOLUME 2 HANDLING AND SERVICING ...

Page 2: ...pter operation or maintenance is forbidden without prior written authorization from Bell Helicopter Textron Inc PN Rev 20 20 SEP 2013 Export Classification C ECCN EAR99 DESTINATION CONTROL STATEMENT WARNING This document contains technical data whose export is restricted by the Arms Export Control Act Title 22 U S C Sec 2751 et seq or the Export Administration Act of 1979 as amended Title 50 U S C...

Page 3: ...LL PARTS OR PARTS THAT HAVE BEEN REPAIRED USING DATA AND OR PROCESSES NOT APPROVED BY BELL BELL IS NOT RESPONSIBLE FOR ANY PART OTHER THAN THOSE THAT IT HAS APPROVED BEFORE PERFORMING ANY PROCEDURE CONTAINED IN THIS MANUAL YOU MUST INSPECT THE AFFECTED PARTS AND RECORDS FOR EVIDENCE OF ANY MANUFACTURE REPAIR REWORK OR USE OF A PROCESS NOT APPROVED BY BELL IF YOU IDENTIFY OR SUSPECT THE USE OF PART...

Page 4: ...Engineering CSE network please access http www bellhelicopter com support Model 206 or 407 Phone 450 437 2862 or 800 363 8023 U S Canada Fax 450 433 0272 E mail pselight bh com Model 222 230 427 429 or 430 Phone 450 437 2077 or 800 463 3036 U S Canada Fax 450 433 0272 E mail pseinter bh com Model 204 205 212 or 412 Phone 450 437 6201 or 800 363 8028 U S Canada Fax 450 433 0272 E mail psemedium bh ...

Page 5: ...e do and you discover it we would appreciate your telling us about it so that we can change whatever is incorrect or unclear Please be as specific as possible Your complaint or suggestion will be acknowledged and we will tell you what we intend to do You may use the enclosed Customer Feedback form as applicable to inform us where we have erred Your assistance is sincerely appreciated Export Classi...

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Page 7: ...al Number if assigned Date of Issue Date of Last Revision Section Chapter Paragraph Affected Your Feedback Now Reads Should Read Your Name Address Position Telephone No Company Fax No Reference No your initials and date If you choose to mail this form fold in thirds with address exposed tape and mail Export Classification C ECCN EAR99 ...

Page 8: ...TAPE HERE From POSTAGE NECESSARY Product Support Engineering 12 800 rue de l Avenir Mirabel Québec Canada J7J 1R4 FOLD ON DOTTED LINES AND TAPE TAPE HERE Export Classification C ECCN EAR99 ...

Page 9: ...____________________________________________ Future Publications to be mailed to this address Address ____________________________________________________________________ City _______________________________________________________________________ State Province _______________________________________________________________ Zip Postal Code _________________________________________________________...

Page 10: ... MAILED IN THE UNITED STATES COMMERCIAL PUBLICATION DISTRIBUTION CENTER P O BOX 482 FORT WORTH TEXAS 76101 0482 FOLD ON DOTTED LINES AND TAPE BUSINESS REPLY MAIL FIRST CLASS PERMIT NO 1744 FORT WORTH TEXAS Export Classification C ECCN EAR99 ...

Page 11: ...and strict tort delictual liability with respect to work performed by third parties at Purchaser s request and with respect to engines engine accessories batteries radios and avionics except Seller assigns each manufacturer s warranty to Purchaser to the extent such manufacturer s warranty exists and is assignable This warranty shall not apply to any helicopter part which has been repaired or alte...

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Page 13: ...Edges Inspection 12 4 3 Pylon Fluid Mount Inspection 13 4 4 Main Rotor Yoke 2500 Hour Inspection 14 4 5 Main Rotor Blade Inspection 15 4 6 Pylon Fluid Mount Torque Shear Pad Bolt Replacement 16 TABLES Table Page Number Title Number 4 1 Airworthiness Limitations Schedule 6 4 2 Inspection Limitations Schedule 10 Chief Engineering Aircraft Certification Transport Canada The Airworthiness Limitations ...

Page 14: ... APPROVAL SIGNATURE Original 1 15 July 1996 N A 2 30 October 1996 Reissue 16 April 1997 N A Reissue 6 July 1999 1 15 October 1999 N A 2 10 December 1999 N A 3 15 December 1999 4 7 January 2000 N A 5 1 July 2000 N A 6 1 August 2002 N A 7 22 August 2002 N A 8 16 December 2002 N A 9 7 November 2003 N A ...

Page 15: ...11 25 October 2005 N A 12 1 May 2006 N A 13 21 June 2006 14 15 December 2006 N A 15 26 January 2007 N A 16 9 January 2008 17 1 September 2009 N A 18 9 September 2011 N A 19 1 November 2012 REVISION NO DATE OF SIGNATURE APPROVAL SIGNATURE 1 NOV 2012 Rev 19 Page 3 4 ...

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Page 17: ... MADE UNSERVICEABLE OR MARKED IN A CONSPICUOUS MANNER TO PREVENT CONTINUED USE EVEN INADVERTENT USE WHEN A REPLACEMENT PART IS INSTALLED THE PART NAME PART NUMBER SERIAL NUMBER AND CURRENT OPERATING HOURS IF APPLICABLE MUST BE RECORDED IN THE HISTORICAL SERVICE RECORD FOR THE ASSEMBLY OR HELICOPTER NOTE The requirements stated in Chapter 5 are to be complied with and the appropriate maintenance ac...

Page 18: ...components and assemblies are determined by experience tests and the judgment of Bell Helicopter engineers The lives cannot be changed without the approval of the Minister of Transport Canada Prior to disposing of unsalvageable helicopter parts and materials caution should be exercised to ensure that the parts and material are disposed of in a manner that does not allow them to be returned for ser...

Page 19: ... Lever Assembly 430 010 405 105 10 000 Collective Idler Link Assembly 430 010 407 101 10 000 Cyclic Lever Assembly 430 010 406 101 10 000 Actuator Support Assembly 222 040 125 001 5000 CONTROL SYSTEM BOLTS AND PINS Pitch Horn to Universal Bolt 50 047C6 36 5000 Universal to Pitch Link Bolt 50 047C6 28 5000 Pitch Link to Rotating Ring Bolt 50 047C6 32 5000 Drive Hub to Drive Hub Bolt 20 057C5 19 500...

Page 20: ...Pin 430 310 455 101 5000 TAIL ROTOR AND CONTROLS Tail Rotor Blade Assembly 222 016 001 123 5000 Tail Rotor Yoke Assembly 222 012 702 109 5000 Tail Rotor Trunnion Assembly 222 012 703 107 5000 TRANSMISSION AND DRIVE SYSTEM Main Rotor Mast Assembly 430 040 130 101 10 000 Tail Rotor Output Shaft 222 042 402 005 5000 PYLON SYSTEM Pylon Fluid Mount 430 310 200 103 105 107 10 000 FIRE PROTECTION SYSTEM ...

Page 21: ...o all successive dash numbers for that component unless otherwise specified Cartridge shall be replaced upon reaching 6 years from date of manufacture Life begins at the manufacture date first hydrostatic test date as marked on reservoir Pylon mounts 430 310 200 103 105 and 107 are subject to airworthiness inspection limitations Table 4 2 Life is from date of manufacture 1 2 3 4 5 ...

Page 22: ...s to all successive dash numbers for that component unless otherwise specified Refer to Chapter 5 for inspection check sheets Inspection applies to yokes with cracks greater than 3 0 inches 76 19 mm Inspection is limited to arm which has crack s greater than 3 0 inches 76 19 mm Refer to Figure 4 1 Refer to Figure 4 2 for inspection details Inspection applies to yokes with cracks less than 3 0 inch...

Page 23: ...on Inspect surfaces for spanwise crack damage between yoke stations 23 0 and 31 0 Inspection applies to yokes with cracks Inspection is limited to arm that has crack s Refer to BHT 430 CR O 2 Chapter 62 for damage criteria NOTES 1 1 1 STATION 31 0 STATION 55 0 STATION 23 0 STATION 0 0 A A SECTION A A 430_MM_04_0001 1 2 3 1 1 1 ...

Page 24: ...BHT 430 MM 2 TC APPROVED 4 00 00 Page 12 Rev 19 1 NOV 2012 ECCN EAR99 Figure 4 2 Main Rotor Yoke Edges Inspection ...

Page 25: ...TC APPROVED BHT 430 MM 2 4 00 00 1 NOV 2012 Rev 19 Page 13 ECCN EAR99 Figure 4 3 Pylon Fluid Mount Inspection ...

Page 26: ...2500 Hour Inspection Refer to BHT 430 CR O Chapter 62 for inspection and damage criteria 1 2 3 Remove main rotor yoke Clean main rotor yoke Perform a detail visual inspection of the entire yoke for evidence of cracking delamination and damage Specific attention should be applied to the shaded areas ...

Page 27: ...TC APPROVED BHT 430 MM 2 4 00 00 1 NOV 2012 Rev 19 Page 15 ECCN EAR99 Figure 4 5 Main Rotor Blade Inspection ...

Page 28: ...BHT 430 MM 2 TC APPROVED 4 00 00 Page 16 Rev 19 1 NOV 2012 ECCN EAR99 Figure 4 6 Pylon Fluid Mount Torque Shear Pad Bolt Replacement ...

Page 29: ...on Event 2 5 00 00 31 5 18 Progressive Inspection Event 3 5 00 00 35 5 19 Progressive Inspection Event 4 5 00 00 39 5 20 Progressive Inspection Event 5 5 00 00 45 5 21 Progressive Inspection Event 6 5 00 00 49 5 22 Progressive Inspection Event 7 5 00 00 53 5 23 Progressive Inspection Event 8 5 00 00 59 5 24 Progressive Inspection Event 9 5 00 00 63 5 25 Progressive Inspection Event 10 5 00 00 67 5...

Page 30: ...er 100 Hours of Operation Following Each Installation 5 00 00 113 CONDITIONAL INSPECTIONS 5 45 Conditional Inspections 5 00 00 115 5 46 Hard Landing 5 00 00 117 5 47 Sudden Stoppage Power ON or OFF 5 00 00 125 5 48 Overtorque 5 00 00 133 5 49 One Engine Inoperative OEI 5 00 00 139 5 50 Lightning Strike 5 00 00 143 5 51 Overspeed 5 00 00 147 5 52 Compressor Stall or Surge 5 00 00 149 COMPONENT OVER...

Page 31: ...r Textron engineers They are subject to change only by Bell Helicopter Textron or an approved airworthiness authority Changes to TBO will be introduced by either revision to the Maintenance Manual Chapter 5 or a Technical Bulletin Every calendar and hourly inspection is a thorough visual inspection to determine the airworthiness of the helicopter and components Qualified persons must do the inspec...

Page 32: ...s a Scheduled inspections must occur at specified operating intervals The intervals may be in operating time hours cycles torque events R I N calendar days months years or other assigned units This makes sure that the helicopter is airworthy b Special inspections are of a temporary nature or of a special interval not consistent with the scheduled inspections c Conditional inspections do not occur ...

Page 33: ... Historical Service Records or in the helicopter logs The operating time is defined as Time in service flight time The measured time which starts the moment the helicopter leaves the ground until it touches the ground at the next point of landing The time when the helicopter is on the ground with the engine and the rotor turning is not included Calendar time The elapsed time which starts on the da...

Page 34: ... T1 T2 W1 W2 430_MM_05_0001 Left engine Right engine Left forward fuselage Right forward fuselage Left aft fuselage Right aft fuselage Left pylon Right pylon Main rotor Tail rotor Left tailboom Right tailboom Left wing Right wing F2 F1 F1 F4 F3 F3 F5 F5 F6 F5 F6 W1 W1 W2 F2 F1 W1 W2 E2 E1 E1 T1 T1 T2 R2 R1 ...

Page 35: ...ections interim inspections or overhaul intervals required beyond the stated tolerances must be approved by Product Support Engineering NOTE The following is only applicable for those operators whose governing aviation authority requires to specifically approve the inspection and overhaul tolerance If approval of the inspection and overhaul tolerance is required by the applicable governing aviatio...

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Page 37: ... You must do a minimum of one complete 50 hour 150 hour and 600 hour inspection within 12 months 5 10 Airframe Progressive The requirements of the airframe periodic 50 hour 150 hour and 600 hour inspections are combined in 12 separate events of similar workload and are done at 50 hour intervals You must do the events in the sequence shown in Table 5 1 After you complete event 12 the progressive cy...

Page 38: ...ave been established for those items to be inspected at intervals other than those established for aircraft periodic inspections Do the scheduled component inspections at every interval that follows 100 hours 300 hours 600 hours or 6 months 600 hours or 12 months 600 hours 1200 hours 2500 hours 6 months 2 years 3 years 5 years ...

Page 39: ...orn or frayed cables make sure there are no loose or broken clamps or fasteners NOTE It is recommended to interrogate the IIDS maintenance pages on both IIDS screens and the engines ECU on a weekly basis mandatory at 50 hour inspection for any recorded fault codes or exceedances 2 Interrogate the Integrated Instrument Display System IIDS for any maintenance advisory flag fault codes or exceedance ...

Page 40: ...mage and to make sure the linkage is correctly attached Examine the doors for cracks in the skin near the hinges F1 F2 Chapter 32 and BHT 430 CR O V 1 5 If retractable landing gear is installed examine the nose landing gear for damage and the extend retract and downlock actuators for leaks Examine the tire for correct pressure and wear Examine the wheel for cracks and to make sure it is serviceabl...

Page 41: ...apter 64 and BHT ALL SPM 11 Examine the tail rotor pitch links for worn bearings and freedom of operation R2 NOTE Clean the main and tail rotor blades more frequently if operating in a corrosive environment or in extreme environmental conditions Chapter 62 and Chapter 64 12 Clean the main and tail rotor blades Make sure the drain hole located on the lower surface of the main rotor blade outboard o...

Page 42: ...d examine damage Chapter 62 b Examine the yoke assembly for cracks and delamination Chapter 62 c Examine the adapters and upper stop assemblies for damage and deformations Chapter 62 d Examine the lead lag dampers for delamination and general condition e Prior to main rotor blade installation remove contact evidence from up stop end plug and replace adapter lead lag pads as required SCHEDULED INSP...

Page 43: ...operating time or a minimum of once every 12 months whichever comes first GENERAL 1 Examine all of the electrical wiring open to view for worn or frayed cables Make sure there are no loose or broken clamps or fasteners Rolls Royce 250 C40B Operation and Maintenance Manual Publication CSP 21000 2 Do the applicable engine inspection Chapter 12 3 Lubricate the helicopter as necessary DETAIL Chapter 2...

Page 44: ...HT 430 FM 1 7 Examine the placards and instrument panel decals Make sure all of the instrument markings are clear and legible F1 F2 Chapter 53 8 Examine the condition of the electrical and avionics components in the nose compartment Make sure they are correctly installed Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners 9 Examine the nose compart...

Page 45: ... O 2 14 Inspect hydraulic actuator support attaching nuts for proper torque R1 Chapter 62 15 Examine the cyclic and collective control levers collective idler link swashplate assembly drive hub assembly drive link assembly and idler link assembly for interference looseness mechanical damage or corrosion Make sure they are correctly attached R1 16 Examine the main rotor hub for damage and correct i...

Page 46: ...d prior to returning helicopter for service Chapter 63 20 Examine the transmission for correct fluid level and leaks F5 F6 Chapter 63 and Chapter 96 21 Remove the transmission chip detectors Examine and clean the chip detectors Install the chip detectors Perform an operational check of each chip detector Chapter 63 22 Examine the main driveshaft over temperature indicators on the transmission and ...

Page 47: ... pylon fluid mount assemblies for corrosion damage and correct fluid level indication Make sure they are correctly attached F5 F6 Chapter 63 and BHT 430 CR O 2 27 Examine the upper and lower lift link rod end bearings for serviceability F5 F6 Chapter 63 28 Examine the left longitudinal restraint spring and support for damage Make sure they are correctly attached F5 Chapter 63 29 Examine the right ...

Page 48: ... overstress E1 Chapter 71 and BHT 430 CR O V 2 36 Examine the left oil cooler blower for blockage cleanliness and damage Make sure it is correctly attached E1 Chapter 65 37 Examine the forward tail rotor driveshaft hanger assembly for cracks at the mount ears corrosion or mechanical damage Make sure it is correctly attached Examine the bearing for discoloration caused by an overheat condition If a...

Page 49: ...c actuator supports for corrosion and mechanical damage Examine the actuator for hydraulic leaks and worn bearings Make sure it is correctly attached F4 Chapter 65 44 Examine the hangar assemblies of the tail rotor driveshaft for cracks at the mount ears corrosion or mechanical damage Make sure they are correctly attached Examine the bearings for discoloration caused by an overheat condition If ap...

Page 50: ...f the nut moves below the lowest value of specified torque range proceed with 2 Year Inspection T1 T2 NOTE Examine inspection window s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter to service Chapter 12 and Chapter 65 50 Remove the tail rotor gearbox fairing and examine the tail rotor ...

Page 51: ...he tail rotor hub and blades are clean Examine the blades for damage Examine the pitch change bearings trunnion bearings and pitch link bearings for looseness Make sure the pitch horns and pitch links are correctly attached R2 Chapter 64 55 Make sure that the tail rotor hub and blade assembly retaining nut has the correct torque R2 Chapter 71 and Chapter 79 56 Examine the right power plant area fo...

Page 52: ...sion wrinkles or other signs of overstress E2 Chapter 79 and BHT 430 CR O V 2 60 Examine the right oil cooler blower for blockage cleanliness and damage Make sure it is correctly attached E2 Rolls Royce 250 C40B Operation and Maintenance Manual Publication CSP 21000 61 Start the helicopter BHT 430 FM 1 and do a FADEC manual mode check SCHEDULED INSPECTIONS 5 14 150 HOUR INSPECTION CONT DATA REFERE...

Page 53: ...F2 Chapter 12 and Chapter 67 2 Remove the left center and right bottom access panels from below the crew compartment Examine the control tubes links rod end bearings bellcranks supports and attach bolts for corrosion and wear Make sure they are correctly attached Make sure the spring cartridges and rotary actuators are correctly attached F1 F2 Chapter 67 3 Measure the amount of minimum friction on...

Page 54: ...nd the emergency exit windows in the passenger doors Examine the emergency exit windows as follows F3 F4 Chapter 52 a Examine the bond between the window retainer and the door frame Replace the retainer if it is not correctly bonded to the frame at all points except at the two lower corners b Examine the inboard and outboard side of all of the rubber retainers Replace the retainers if you find any...

Page 55: ...s are located install support assembly Chapter 67 10 Remove the aft fuselage access panel Examine the control tube bellcrank and support assembly for corrosion mechanical damage and worn bearings and clevises Make sure they are correctly attached F4 Chapter 67 and BHT 430 CR O 4 11 Remove the tail rotor control tube Examine the control tube nylatron sleeves at the four areas where the tube contact...

Page 56: ...utboard surface of the yoke for deformation Deformed washers must be replaced Chapter 53 15 Remove the fairing cover plates and examine the wing s to fuselage attach points for corrosion looseness and damage Check torque of attaching bolts nuts Chapter 53 16 Remove baggage compartment floor and examine the following a Examine surrounding aft fuselage structure for corrosion and damage b Examine wi...

Page 57: ... Chapter 96 1 Remove the access panel from the aft electrical compartment Examine the condition of the electrical and avionics components and make sure they are correctly attached Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners F4 Chapter 96 2 Remove the battery Examine the vent lines for blockage or damage Clean the battery area before you ins...

Page 58: ...holes corrosion wrinkles or other signs of overstress E1 E2 Chapter 63 and Chapter 79 7 Examine the transmission and engine oil coolers for blockage and oil leaks Make sure they are correctly attached E1 E2 Chapter 65 8 Examine the hangar assemblies of the tail rotor driveshaft for cracks at the mount ears corrosion or mechanical damage Make sure they are correctly attached Examine the bearing for...

Page 59: ... of specified torque range If the nut moves below the lowest value of specified torque range proceed with 2 Year Inspection T1 T2 NOTE Examine inspection window s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter for service Chapter 12 and Chapter 65 14 Remove the tail rotor gearbox fairin...

Page 60: ...rn counterweight bellcrank bearings e Check for worn inner race in the tail idler assembly f Check for unbonded bearing in the upper leg of tail rotor input lever assembly g Check for worn bearings in the tail rotor pitch links Chapter 64 18 Make sure that the tail rotor hub and blades are clean Examine the blades for damage Examine the pitch change bearings and trunnion bearings for looseness Mak...

Page 61: ...TE Examine inspection window s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter for service Chapter 63 1 Examine the left and right pylon fluid mounts for corrosion damage and correct fluid level Make sure they are correctly attached F5 F6 Chapter 63 and BHT 430 CR O 2 2 Examine the upper...

Page 62: ...or discoloration Examine the driveshaft coupling and surrounding area for slung grease R1 Chapter 63 9 Examine the main driveshaft over temperature indicators on the transmission and engine end driveshaft couplings for discoloration Examine the driveshaft couplings and surrounding area for slung grease R1 NOTE Examine inspection window s and sight glass es for cracking and discoloration If either ...

Page 63: ...d contact Bell Helicopter Product Support Engineering for instructions Chapter 62 16 Examine the damper blade sets and the shear restraints elastomer for delamination wear crumbling or damage Examine the fluidlastic dampers and surrounding area for signs of leakage Verify that the gold pin in each pressure indicator extends above the black sleeve or the bottom of the metal cap plastic window Exami...

Page 64: ...s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter for service Chapter 29 20 Examine the hydraulic lines for leaks Examine the color and level of the fluid in the PC 1 system and PC 2 system reservoirs Examine the module pressure and return filters for impending bypass indication Make sur...

Page 65: ...t Make sure they are correctly installed Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners Chapter 52 2 Examine the nose compartment door for damage Make sure it latches correctly F1 F2 Chapter 95 3 Examine the pitot tubes Make sure they are correctly attached F1 F2 Chapter 52 4 Examine the crew doors passenger doors and baggage compartment doors...

Page 66: ...NE COMPRESSOR SECTION Chapter 71 11 Examine both of the engine inlet screens for damage F5 F6 Chapter 71 12 Examine all of the firewalls and fire shields for cracks distortion loose or missing rivets broken spot welds and deterioration of the seals and sealant E1 E2 Chapter 71 13 Examine the left power plant area for fuel or oil leaks Examine the wire harness and the flexible and rigid fuel and oi...

Page 67: ...ey are correctly attached E2 Chapter 76 20 Examine the right engine power lever fuel control box assembly and control cable for looseness and correct range of motion Make sure they are correctly attached E2 Chapter 63 21 Examine the right oil cooler blower driveshaft and couplings for damage Make sure they are correctly attached Examine the discs for cracks that radiate from the bolt holes corrosi...

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Page 69: ... Chapter 96 1 Remove the access panel from the aft electrical compartment Examine the condition of the electrical and avionics components and make sure they are correctly attached Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners F4 Chapter 96 2 Remove the battery Examine the vent lines for blockage or damage Clean the battery area before you ins...

Page 70: ...holes corrosion wrinkles or other signs of overstress E1 E2 Chapter 63 and Chapter 79 7 Examine the transmission and engine oil coolers for blockage and oil leaks Make sure they are correctly attached E1 E2 Chapter 65 8 Examine the hangar assemblies of the tail rotor driveshaft for cracks at the mount ears corrosion or mechanical damage Make sure they are correctly attached Examine the bearing for...

Page 71: ...ct upper surface for any cracks corrosion or working rivets d If no cracks corrosion or working rivets are located install support assembly e Remove lower support assembly Save attaching hardware f Clean lower surface of stabilizer g With bright light inspect lower surface for any cracks corrosion or working rivets h If no cracks corrosion or working rivets are located install support assembly 13 ...

Page 72: ...e Chapter 12 and Chapter 65 15 Remove tail rotor gearbox fairing and examine the tail rotor gearbox for oil leaks and mechanical or corrosion damage Make sure the gearbox has the correct fluid level Make sure the gearbox is correctly attached R2 16 Inspect tail rotor gearbox retaining nuts for proper torque Chapter 65 17 Remove the tail rotor gearbox chip detector Clean and examine the chip detect...

Page 73: ... torque R2 BHT 430 CR O 3 21 Make sure that the tail rotor blades attaching bolts nuts have the correct torque R2 22 Inspect tail rotor blades pitch change bearings as follows a Without removing the blade clean exposed areas of pitch change bearings BHT 430 CR O 3 b With the blade bolts torqued to the highest value of torque range visually inspect each bearing inner member neck area full 360 for c...

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Page 75: ...TE Examine inspection window s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter for service Chapter 63 1 Examine the left and right pylon fluid mounts for corrosion damage and correct fluid level Make sure they are correctly attached F5 F6 Chapter 63 and BHT 430 CR O 2 2 Examine the upper...

Page 76: ...tors for discoloration Examine the driveshaft coupling and surrounding area for slung grease R1 Chapter 63 9 Examine the main driveshaft over temperature indicators on the transmission and engine end driveshaft couplings for discoloration Examine the driveshaft couplings and surrounding area for slung grease R1 NOTE Examine inspection window s and sight glass es for cracking and discoloration If e...

Page 77: ...act Bell Helicopter Product Support Engineering for instructions Chapter 62 16 Examine the damper blade sets and the shear restraints elastomer for delamination wear crumbling or damage Examine the fluidlastic dampers and surrounding area for signs of leakage Verify that the gold pin in each pressure indicator extends above the black sleeve or the bottom of the metal cap plastic window Examine the...

Page 78: ... service Chapter 29 19 Examine the hydraulic lines for leaks Examine the color and level of the fluid in the PC 1 system and PC 2 system reservoirs Examine the module pressure and return filters for impending bypass indication Make sure that the flexible hoses are in good condition and do not show signs of chafing F5 F6 SCHEDULED INSPECTIONS 5 20 PROGRESSIVE INSPECTION EVENT 5 CONT DATA REFERENCE ...

Page 79: ...t Make sure they are correctly installed Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners Chapter 52 2 Examine the nose compartment door for damage Make sure it latches correctly F1 F2 Chapter 95 3 Examine the pitot tubes Make sure they are correctly attached F1 F2 Chapter 52 4 Examine the crew doors passenger doors and baggage compartment doors...

Page 80: ...PRESSOR SECTION Chapter 71 11 If installed examine both of the engine inlet screens for damage F5 F6 Chapter 71 12 Examine all of the firewalls and fire shields for cracks distortion loose or missing rivets broken spot welds and deterioration of the seals and sealant E1 E2 Chapter 71 13 Examine the left power plant area for fuel or oil leaks Examine the wire harness and the flexible and rigid fuel...

Page 81: ...ey are correctly attached E2 Chapter 76 20 Examine the right engine power lever fuel control box assembly and control cable for looseness and correct range of motion Make sure they are correctly attached E2 Chapter 63 21 Examine the right oil cooler blower driveshaft and couplings for damage Make sure they are correctly attached Examine the discs for cracks that radiate from the bolt holes corrosi...

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Page 83: ... Chapter 96 1 Remove the access panel from the aft electrical compartment Examine the condition of the electrical and avionics components and make sure they are correctly attached Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners F4 Chapter 96 2 Remove the battery Examine the vent lines for blockage or damage Clean the battery area before you ins...

Page 84: ...shaft hanger coupling for cracks that radiate from the bolt holes corrosion wrinkles or other signs of overstress E1 E2 Chapter 63 and Chapter 79 7 Examine the transmission and engine oil coolers for blockage and oil leaks Make sure they are correctly attached E1 E2 Chapter 65 8 Examine the hangar assemblies of the tail rotor driveshaft for cracks at the mount ears corrosion or mechanical damage M...

Page 85: ...ge Make sure they are correctly attached T1 T2 CAUTION REFER TO CHAPTER 53 TABLE 53 1 FOR CORRECT TORQUE Chapter 53 14 Examine the vertical fin assembly for damage Make sure the vertical fin attach bolts nuts have the correct torque Apply torque in the tightening direction to the nut while restraining the bolt head If the lowest value of specified torque range is reached without nut movement raise...

Page 86: ...rol tube nylatron sleeves at the four areas where the tube contacts the tailboom fairleads and the heat shrink at the two ends of the control tube T1 T2 NOTE Examine inspection window s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter to service Chapter 12 and Chapter 65 18 Examine the ta...

Page 87: ...ings e Check for worn inner race in the tail rotor idler assembly f Check for unbonded bearing in the upper leg of tail rotor input lever assembly g Check for worn bearings in the tail rotor pitch links Chapter 64 22 Make sure that the tail rotor hub and blades are clean Examine the blades for damage Examine the pitch change bearings and trunnion bearings for looseness Make sure the pitch horns ar...

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Page 89: ...TE Examine inspection window s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter for service Chapter 63 1 Examine the left and right pylon fluid mounts for corrosion damage and correct fluid level Make sure they are correctly attached F5 F6 Chapter 63 and BHT 430 CR O 2 2 Examine the upper...

Page 90: ...or discoloration Examine the driveshaft coupling and surrounding area for slung grease R1 Chapter 63 9 Examine the main driveshaft over temperature indicators on the transmission and engine end driveshaft couplings for discoloration Examine the driveshaft couplings and surrounding area for slung grease R1 NOTE Examine inspection window s and sight glass es for cracking and discoloration If either ...

Page 91: ... contact Bell Helicopter Product Support Engineering for instructions Chapter 62 16 Examine the damper blade sets and the shear restraints elastomer for delamination wear crumbling or damage Examine the fluidlastic dampers and surrounding area for signs of leakage Verify that the gold pin in each pressure indicator extends above the black sleeve or the bottom of the metal cap plastic window Examin...

Page 92: ... service Chapter 29 19 Examine the hydraulic lines for leaks Examine the color and level of the fluid in the PC 1 system and PC 2 system reservoirs Examine the module pressure and return filters for impending bypass indication Make sure that the flexible hoses are in good condition and do not show signs of chafing F5 F6 SCHEDULED INSPECTIONS 5 23 PROGRESSIVE INSPECTION EVENT 8 CONT DATA REFERENCE ...

Page 93: ...e the control tubes links rod end bearings bellcranks supports and attach bolts for corrosion and wear Make sure they are correctly attached Make sure the spring cartridges and rotary actuators are correctly attached F1 F2 Chapter 12 2 Remove the access panels along the bottom centerline of the fuselage F3 F4 Chapter 67 a Examine the directional control tubes rod end bearings bellcranks supports a...

Page 94: ...r tears or separations Make sure the doors are correctly attached to the airframe structure F1 F2 F3 F4 Chapter 25 8 Examine the seat cushions and seat backs for tears and deterioration Make sure they are correctly attached F1 F2 F3 F4 Chapter 25 9 Examine the seat assemblies to make sure they are correctly attached to airframe structure F1 F2 F3 F4 Chapter 25 10 Examine the crew seat attenuation ...

Page 95: ...e left engine power lever fuel control box assembly and control cable for looseness and correct range of motion Make sure they are correctly attached E1 Chapter 63 19 Examine the left oil cooler blower driveshaft and couplings for damage Make sure they are correctly attached Examine the discs for cracks that radiate from the bolt holes corrosion wrinkles or other signs of overstress E1 Chapter 79 ...

Page 96: ...rrectly attached Examine the discs for cracks that radiate from the bolt holes corrosion wrinkles or other signs of overstress E2 Chapter 79 and BHT 430 CR O V 2 25 Examine the right oil cooler blower for blockage cleanliness and damage Make sure it is correctly attached E2 Rolls Royce 250 C40B Operation and Maintenance Manual Publication CSP 21000 26 Start the helicopter BHT 430 FM 1 and do a FAD...

Page 97: ...TAIL Chapter 96 1 Remove the access panel from the aft electrical compartment Examine the condition of the electrical and avionics components and make sure they are correctly attached Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners F4 Chapter 95 2 Remove the battery Examine the vent lines for blockage or damage Clean the battery area before you...

Page 98: ...corrosion wrinkles or other signs of overstress E1 E2 Chapter 63 and Chapter 79 7 Examine the transmission and engine oil coolers for blockage and oil leaks Make sure they are correctly attached E1 E2 Chapter 65 8 Examine the hangar assemblies of the tail rotor driveshaft for cracks at the mount ears corrosion or mechanical damage Make sure they are correctly attached Examine the bearings for disc...

Page 99: ...NOTE Examine inspection window s and sight glass es for cracking and discoloration If either of these conditions are present the part must be removed and replaced prior to returning helicopter for service Chapter 12 and Chapter 65 14 Examine the tail rotor gearbox for oil leaks and mechanical or corrosion damage Make sure the gearbox has the correct fluid level Make sure the gearbox is correctly a...

Page 100: ...ever assembly g Check for worn bearings in the tail rotor pitch links Chapter 64 18 Make sure that the tail rotor hub and blades are clean Examine the blades for damage Examine the pitch change bearings trunnion bearings and pitch link bearings for looseness Make sure the pitch horns and pitch links are correctly attached R2 Chapter 64 19 Make sure that the tail rotor hub and blade assembly retain...

Page 101: ...n Examine the lower and upper cyclic and collective pitch control bellcranks for loose bearings corrosion or mechanical damage to the clevises Make sure they are correctly attached to the supports and control tube bearings F5 F6 Chapter 71 2 Examine the engine control cables and idle stop solenoids for corrosion and damage Make sure they are correctly attached F5 F6 NOTE Examine inspection window ...

Page 102: ...e the brake linings if they are worn more than the acceptable limits Make sure the brake linings are correctly attached Examine the brake disc for damage F3 F4 F5 F6 Chapter 65 and BHT 430 CR O 3 10 Examine the tail rotor driveshaft coupling over temperature indicators for discoloration Examine the driveshaft coupling and surrounding area for slung grease R1 Chapter 63 11 Examine the main drivesha...

Page 103: ...er section center to station 15 as follows R1 a Clean the yoke center sections b Do a careful visual inspection of the yoke center sections for delamination and damage c If any defects are found contact Bell Helicopter Product Support Engineering for instructions Chapter 62 17 Examine the damper blade sets and the shear restraints elastomer for delamination wear crumbling or damage Examine the flu...

Page 104: ... Examine the hydraulic lines for leaks Examine the color and level of the fluid in the PC 1 system and PC 2 system reservoirs Examine the module pressure and return filters for impending bypass indication Make sure that the flexible hoses are in good condition and do not show signs of chafing F5 F6 BHT 430 CR O 2 21 Inspect hydraulic actuator support attaching nuts for proper torque R1 Chapter 53 ...

Page 105: ...50 hour inspection DETAIL Chapter 96 1 Examine the condition of the electrical and avionics components in the nose compartment Make sure they are correctly installed Examine the electrical harnesses and cables for frayed wires and loose or broken clamps and fasteners Chapter 52 2 Examine the nose compartment door for damage Make sure it latches correctly F1 F2 Chapter 95 3 Examine the pitot tubes ...

Page 106: ...are correctly attached F1 F2 F3 F4 Chapter 25 7 Examine the seat assemblies to make sure they are correctly attached to airframe structure F1 F2 F3 F4 Chapter 25 8 Examine the crew seat attenuation indicators F1 F2 Chapter 25 9 Examine the safety belts and shoulder harnesses for deterioration Make sure they are correctly attached to the airframe structure F1 F2 F3 F4 Chapter 26 10 Examine the cabi...

Page 107: ... left engine power lever fuel control box assembly and control cable for looseness and correct range of motion Make sure they are correctly attached E1 Chapter 63 18 Examine the left oil cooler blower driveshaft and couplings for damage Make sure they are correctly attached Examine the discs for cracks that radiate from the bolt holes corrosion wrinkles or other signs of overstress E1 Chapter 79 a...

Page 108: ...rectly attached Examine the discs for cracks that radiate from the bolt holes corrosion wrinkles or other signs of overstress E2 Chapter 79 and BHT 430 CR O V 2 24 Examine the right oil cooler blower for blockage cleanliness and damage Make sure it is correctly attached E2 Rolls Royce 250 C40B Operation and Maintenance Manual Publication CSP 21000 25 Start the helicopter BHT 430 FM 1 and do a FADE...

Page 109: ...______________ _________________________ SWASHPLATE CONTROLS 1 Examine the swashplate assembly Chapter 62 a Remove the pitch change links and disconnect the drive link from the rotating ring R1 NOTE Examine the duplex bearing before you lubricate the swashplate b Rotate the swashplate outer ring and make sure the duplex bearing operates smoothly Replace the bearing if it feels rough Chapter 12 c L...

Page 110: ...de must be removed to perform this inspection BHT 430 CR O 2 Chapter 62 1 Examine the main rotor yokes as follows R1 a Clean the yoke s b Do a visual inspection of the yokes for cracks c Refer to BHT 430 CR O 2 Chapter 62 for damage criteria SCHEDULED INSPECTIONS 5 28 EVERY 100 HOURS OF COMPONENT OPERATION CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Page 111: ...ssembly and rotating controls as follows R1 Chapter 62 a Remove the pitch change links and disconnect the drive link from the rotating ring BHT ALL SPM b Examine the upper pitch link universal bearings for axial play Replace the bearing if it is more than the permitted limits BHT 430 CR O 2 c Examine the lower pitch link rod end for axial and radial play Replace the bearing if one is more than the...

Page 112: ...essary NOTE This inspection does not apply to 430 010 400 103 swashplate configuration with single piece bearing sets and non splitted ball sleeve guide bearings BHT 430 CR O 2 h Examine the area around the upper and lower ball sleeve bearing sets for signs of fretting rotation Chapter 62 i Install the pitch change links and connect the drive link to the rotating ring SCHEDULED INSPECTIONS 5 29 EV...

Page 113: ... ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ ENGINE FIRE EXTINGUISHER AND CARTRIDGE Chapter 26 and Chapter 96 1 Examine the right engine fire extinguisher for dents and scratches Perform operational check of engine fire extinguisher system F4 Chapter 26 and Chapter 96 2 Examine the left engine fire ex...

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Page 115: ...__ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ MAIN DRIVESHAFT Chapter 12 and BHT 430 CR O 2 1 Examine and lubricate the right main driveshaft E2 2 Examine and lubricate the left main driveshaft E1 TAIL ROTOR DRIVESHAFT Chapter 12 and BHT 430 CR O 3 1 Examine and ...

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Page 117: ...GENERATOR BHT 430 CR O V 2 NOTE The component manufacturer s recommended inspection intervals can be followed as an alternate means of compliance Chapter 96 1 Examine the right engine starter generator brushes for wear down to the diagonal groove wear indicator E2 Chapter 96 2 Examine the left engine starter generator brushes for wear down to the diagonal groove wear indicator E1 PYLON FLUID MOUNT...

Page 118: ...s inspection limitation This inspection only applies to main rotor yokes with cracks less than 3 0 inches 76 19 mm located between station 23 0 and station 31 0 NOTE This inspection is limited to yoke arm s that has crack s less than 3 0 inches 76 19 mm NOTE Main rotor blade must be removed to perform this inspection BHT 430 CR O 2 Chapter 62 1 Examine the main rotor yokes as follows R1 a Clean th...

Page 119: ...move right hydraulic pump Inspect pump drive spline and transmission adapter gear spline for wear F6 SWASHPLATE ASSEMBLY 1 Inspect the swashplate collective lever bushings P N 430 010 423 and cyclic pivot pins P N 430 310 455 as follows Chapter 62 a Remove left and right cyclic lever assemblies P N 430 010 406 from the swashplate assembly b Wipe clean the pin assemblies and the bushing faces to re...

Page 120: ... for overhaul at which time both the bushings and pins will be removed and scrapped Chapter 62 e If the pins and bushings are suitable for return to service reinstall the left and right cyclic lever assemblies P N 430 010 406 on the swashplate assembly SCHEDULED INSPECTIONS 5 33 EVERY 1200 HOURS OF COMPONENT OPERATION CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Page 121: ...______________________________________ SIGNATURE _______________ _________________________ MAIN ROTOR BLADES Chapter 4 NOTE Step 1 is an airworthiness inspection limitation 1 Examine the main rotor blades as follows R1 a Remove the main rotor blades b Clean the main rotor blades c Do a visual inspection of the main rotor blades for delamination and damage d If any defect is found contact Bell Heli...

Page 122: ...is found refer to BHT 430 CR O 2 Chapter 62 for damage criteria PYLON SYSTEM Chapter 4 NOTE Step 1 is an airworthiness inspection limitation Chapter 63 1 Remove and replace one at a time torque shear pad attaching bolts qty 16 SCHEDULED INSPECTIONS 5 34 EVERY 2500 HOURS OF COMPONENT OPERATION CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Page 123: ...Y _________________ _________________________ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ STANDBY ATTITUDE INDICATOR Chapter 95 1 Test the pilot standby attitude indicator power supply F1 F2 26 JAN 2007 Rev 15 Page 93 94 ...

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Page 125: ..._____________ SWASHPLATE AND CONTROLS Chapter 5 and Chapter 62 NOTE Examine the control bolts more frequently if you operate the helicopter in adverse environmental conditions 1 Inspect the flight control bolts R1 a Remove the bolts that follow 1 Remove four bolts from the main rotor pitch link universal bearing upper 2 Remove four bolts from the main rotor pitch link universal bearing lower 3 Rem...

Page 126: ...on Replace damaged bolts Chapter 62 d Apply a film of corrosion preventive compound C 104 to the bolt shanks only Install the bolts e Following bolt s installation torque and safety the bolts Coat the bolt heads and nuts with corrosion preventive compound C 101 MAIN ROTOR MAST BHT 430 CR O 2 1 Examine the main rotor mast internally for corrosion R1 Chapter 62 and BHT 430 CR O 2 Chapter 63 2 Examin...

Page 127: ...ect hardware Tighten hardware 5 inch pounds 0 5649 Nm plus tare Using feeler gauge measure gap at eight locations where vertical fin fitting contacts tailboom fitting Gap shall be less than 0 003 inch 0 076 mm If gap is larger than 0 003 inch 0 076 mm fill gap using shim P N 120 008C40E11 Maximum allowable shim thickness is 0 010 inch 0 254 mm Remove vertical fin CAUTION ATTACHING HARDWARE SHALL B...

Page 128: ...CORRECT TORQUE Chapter 53 7 Install vertical fin to tailboom using bolts washers and nuts Torque nuts 8 Apply corrosion preventive compound C 101 to bolt heads nuts and washers SCHEDULED INSPECTIONS 5 36 EVERY 2 CALENDAR YEARS CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Page 129: ..._____ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ EMERGENCY FLOTATION SYSTEM NOTE This inspection applies to any reservoir cylinder which has been manufactured or last retested prior to July 1 2006 Chapter 99 1 Remove emergency flotation system nitrogen reservoir Perform a hydrostatic test...

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Page 131: ...ns for the time between replacement schedule for the squib Chapter 26 1 Remove the right fire extinguisher reservoir Do a hydrostatic test in accordance with specification DOT 4 DA DOT 4 DS or DOT SP 7945 as marked on container F4 Chapter 26 2 Remove the left fire extinguisher reservoir Do a hydrostatic test in accordance with specification DOT 4 DA DOT 4 DS or DOT SP 7945 as marked on container F...

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Page 133: ...ration following each installation Tail Rotor After 1 to 5 hours of operation following each installation Vertical Fin After 5 to 10 hours of operation following each installation Tail Rotor Hub and Blades After 5 to 10 hours of operation following each installation Hydraulic Actuator Support After 5 to 10 hours of operation following each installation Swashplate After 25 hours of operation follow...

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Page 135: ...__ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ Chapter 4 NOTE This is an airworthiness inspection limitation MAIN ROTOR YOKES 1 With the main rotor blades removed examine the main rotor yokes as follows R1 a Clean the yokes b Do a careful visual inspection of the yokes for cracks delamination and impact damage BHT...

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Page 137: ...hapter 62 NOTE Torque application for the thru bolts and nuts must be performed in a specific sequence MAIN ROTOR YOKES 1 Following each installation verify torque of the eight through bolts and nuts attaching the main rotor yokes to the main rotor mast Repeat the torque verification every 1 to 5 hours until torque stabilize to 60 to 65 foot pounds 81 35 to 88 12 Nm R1 TAIL ROTOR Chapter 64 1 Foll...

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Page 139: ... bolts nuts is correct after a minimum of 5 hours but do not exceed 10 hours of service after each installation Apply highest value of specified torque range to the nut while restraining the bolt head TAIL ROTOR HUB AND BLADES BHT 430 CR O 3 1 Make sure the torque of the tail rotor blades attaching bolts nuts is correct after a minimum of 5 hours but do not exceed 10 hours of operation after each ...

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Page 141: ... FACILITY _________________ _________________________ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ SWASHPLATE Chapter 62 1 Make sure the swashplate friction adjustment is correct 25 hours after the initial installation R1 26 JAN 2007 Rev 1...

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Page 143: ...______ FACILITY _________________ _________________________ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ TAIL ROTOR GEARBOX Chapter 65 1 Make sure the torque of the tail rotor gearbox retaining nuts is correct T1 T2 26 JAN 2007 Rev 15 Page...

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Page 145: ...include but are not limited to the following hard landing sudden stoppage power ON or OFF overtorque lightning strike overspeed compressor stall or surge Evaluate the components that you remove from the helicopter as a result of a conditional inspection as an interrelated group The removal records that go with each component must cross reference the part and serial numbers of the other components ...

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Page 147: ...cts the ground hard enough to cause severe pitch movement of the main rotor The impact can cause cracks or yields to the transmission or fluid mount support structure or unusually high loads on the landing gear A hard landing with a retractable landing gear helicopter is any landing that forces correctly serviced tires and or shock struts to compress to the bottom of travel This also applies to hi...

Page 148: ...er on jacks examine the landing gear as follows a Examine the tires for cuts and damage Make sure they have not deflated NOTE If you find a deformed or cracked wheel remove the wheel and the landing gear assembly for further inspection b Examine the wheel rim for cracks or damage Examine the bolts that connect the wheel rim for damage Make sure that the bolts are not loose Examine the brake assemb...

Page 149: ...e wheel from the fully extended to the fully compressed position Make sure the shock strut does not bind If the shock strut does bind remove the landing gear for further inspection f Raise the landing gears by hand to the retracted position Examine the landing gears for damage and looseness Make sure there is clearance between the landing gear and the wheel well Chapter 32 and Chapter 53 4 If the ...

Page 150: ...ard landing has occurred do step 9 through step 22 9 Examine the transmission and mast as follows NOTE If there is any yielding deformation or damage the mast is unserviceable and not repairable a Examine the mast for signs of yielding or deformation b Examine the transmission mount points for cracks loose sheared or elongated rivets studs or bolts or other damage Pay particular attention to the a...

Page 151: ...ssemblies for cracks debonding or other damage 4 Examine the static stops and main rotor adapters for deformation and damage BHT 430 CR O 2 11 If you found any damage when you did step 9 and step 10 remove and do an overhaul of the components that follow a Mast assembly b Transmission assembly 1 Remove and scrap the transmission top case assembly c Main drive shaft assemblies 12 Make sure that all...

Page 152: ... airframe expand the inspection in that area until you get past the zone of damage Rolls Royce 250 C40B Operation and Maintenance Manual Publication CSP 21000 17 Do an engine hard landing inspection 18 Do a complete inspection and rigging check of the flight control system from the cockpit controls to the main rotor head Examine the system for bent or damaged control tubes damage to the actuator s...

Page 153: ...and should be replaced 22 Do a full visual inspection of the components that follow If you do not find any problems or damage to the components they may be kept in service a Tail rotor hub and controls b Tail rotor gearbox c Tail rotor driveshafts d Tail rotor driveshaft hangar assemblies e Tail rotor blades f Main rotor blades CONDITIONAL INSPECTIONS 5 46 HARD LANDING CONT DATA REFERENCE INSPECTI...

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Page 155: ...system A blade strike is a rapid deceleration of the drive system due to contact of the main or tail rotor blades with the ground water snow dense vegetation or any other object sufficient to cause any of the damage that follows Main Rotor Blades Any impact damage to the leading edge or lower skin which exceeds the limits specified in the BHT 430 CR O Any skin cracks Main Rotor Mast Twisting out o...

Page 156: ...a Main rotor blades 1 Examine the main rotor blades for damage such as cracks bond voids and delamination 2 If you find damage on any blade return all blades to an authorized overhaul facility Make an entry in the component record to show that the reason for removal was a sudden stoppage 3 You may keep all blades in service if no damage was found on any blade b Main rotor yokes 1 You may keep the ...

Page 157: ...iscrepancies in step c 1 do a close visual inspection of the main rotor controls You can keep the swashplate and drive hub idler link and drive link assemblies in service if you do not find any signs of damage 3 Replace all of the bolts in the rotating controls Scrap the removed bolts d Main driveshafts 1 Remove and visually examine the main driveshafts If you find signs that the driveshaft is ben...

Page 158: ...rable do an overhaul of the mast and transmission Remove and scrap the transmission top case Make an entry in the component record to show that the reason for removal was a sudden stoppage g Tail rotor driveshaft system 1 Visually examine the tail rotor driveshaft tubes Make sure they are not bent or twisted 2 Remove the gear coupling assembly at the transmission tail rotor output quill Disassembl...

Page 159: ...rike a Tail rotor driveshaft hangers and coupling 1 Examine all of the tail rotor driveshaft hangers If a shaft has been damaged by a main rotor strike or any other circumstance other than torsional overload replace the hangers that the damaged shaft was attached to If any shaft fails because of a torsional overload remove and scrap all the hangers couplings and driveshafts 2 Remove the gear coupl...

Page 160: ...e results of step a or step b above do a thorough inspection of the hanger support structure for cracks loose or sheared rivets and elongated holes Chapter 65 2 If you do not find any of the conditions that are listed in step a through step d examine the tail rotor driveshafts Make an entry in the component records to show that the reason for removal was a sudden stoppage c Tail rotor hub and blad...

Page 161: ...irleads and the bearings Closely examine the support bellcranks and links installed on the tail rotor gearbox 3 Examine the tailboom structure for distortion cracks loose or sheared rivets Closely examine the tail rotor driveshaft support structure and the tailboom to fuselage attach area f If you replaced the tail rotor gearbox tail rotor driveshaft or the tail rotor driveshaft hanger assemblies ...

Page 162: ...earing if it is rough or damaged 4 Examine the center bearing case roller bearing Replace the bearing if it is rough or damaged BHT 430 CR O 2 5 Do an overhaul of the tail rotor drive quill CONDITIONAL INSPECTIONS 5 47 SUDDEN STOPPAGE POWER ON OR OFF CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Page 163: ...s greater than the allowed limits are applied into the helicopter dynamic system NOTE No action is required if overtorque is within 100 to 105 Refer to the Rolls Royce 250 C40B Operation and Maintenance Manual Publication 21000 for the engine overtorque limits and the inspection requirements 1 When the overtorque is more than 105 but not more than 115 do the steps that follow a Do a thorough visua...

Page 164: ...rical dimension between any of the three lengthwise locations as an average of the three azimuth measurements in each location shall not be greater than 0 010 inch 0 25 mm and not less than 3 445 inches 875 mm 4 Lift link lower attach fittings 5 Pylon fluid mounts 6 Transmission restraints and restraint fittings 7 Transmission top case 8 Examine the main driveshaft couplings for signs that they ov...

Page 165: ...e do a thorough visual inspection of the systems that follow 1 Main rotor yoke assembly 2 Main rotor mast 3 Transmission top case 4 Pylon fluid mounts 5 Cabin roof at the transmission lift link attach points 6 Transmission restraint attachment at the stop mounts support and the cabin roof shell and beam 7 Transmission electric chip detectors 8 Tail rotor hub blades and attachments 9 Swashplate and...

Page 166: ...ded engine No 1 and or engine No 2 torque history shows no excursions above published OEI limits Verify engine s history as follows NOTE The IIDS and FADEC system must be self tested to confirm proper functioning Self test is performed every time power is applied to the helicopter a Verify proper functioning of both IIDS and FADEC system SHOULD THE IIDS OR FADEC FAIL SELF TEST BOTH OUTBOARD QUILLS...

Page 167: ...ction of the systems that follow 1 Main rotor yokes and blades 2 Pylon fluid mounts and lift links 3 Cabin roof at the transmission lift link fittings 4 Transmission restraint attachments 5 Transmission electric chip detectors 6 Tail rotor hub blades and attachments 7 Swashplate and levers assembly 8 Drive hub drive link and idler link assemblies 9 Tail rotor driveshafts couplings and bearings CON...

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Page 169: ...__________ NOTE The Integrated Display System IIDS records any OEI events 2 minutes 30 seconds and OEI MGT TORQUE peaks total duration and date of occurrence for each engine 1 When an OEI event has been recorded perform the following Chapter 95 a Verify the maintenance pages of both IIDS screens for any exceedances Review ECU engine faults engine exceedances and engine history data pages NOTE Full...

Page 170: ...uired BHT 430 FM 1 NOTE An OEI overtorque is an incident where engine torque is greater than the allowed limits as follows Operation at 98 to 105 3 engine torque for period greater than 2 minutes continuous Operation at or above 105 3 engine torque for period greater than 30 seconds continuous Operation above 109 6 engine torque with FADEC in Manual MODE Degraded MODE or Failed Fixed MODE Operatio...

Page 171: ...intenance Manual Publication CSP 21000 d Perform engine overtorque inspection as required BHT 430 CR O 2 e Disassemble the main transmission and do an overhaul inspection of the transmission subassemblies that follow 1 Center bearing case gearshaft support case 2 Collector gear shaft 3 Power on side outboard quill 4 Power on side input quill f Do an overhaul of the power on side main driveshaft CO...

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Page 173: ...e in any area of the airframe expand the inspection in that area until you get past the zone of damage 1 Examine all of the external surfaces of the helicopter Closely examine the main rotor blades main rotor yokes transmission mast assembly tail rotor blades and hub tail rotor gearbox horizontal stabilizer auxiliary fins and the vertical fin Examine the electrical instruments and systems 2 If you...

Page 174: ...rned or debonded f Remove the tail rotor driveshaft bearing hangers and the tail rotor gearbox and return them for overhaul Make an entry in the component record to show that the reason for removal was a lightning strike g Examine the auxiliary fins for signs of burns or that they are debonded h Examine the tailboom fitting for signs of arc burns around the mount points of the tail rotor gearbox a...

Page 175: ...ull service If you do find metal particles remove the transmission and mast assembly and return it for overhaul Make an entry in the component record to show that the reason for removal was a lightning strike c Remove the output quill assembly from the tail rotor gearbox Examine the gear teeth for signs of electrical arcs or burns Make sure that the bearing turns smoothly 1 If you find arcs or bur...

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Page 177: ... 21000 Rotor overspeed is any incident where the main rotor speed goes past 109 Refer to engine operation and maintenance manual for the overspeed limits and inspection procedures 1 If the main rotor speed goes above 109 but not more than 120 visually examine the following components If no damage is found no further inspection is required a Main rotor yokes and blades b Swashplate and levers assem...

Page 178: ...the main rotor overspeed goes above 120 remove and overhaul the components that follow Make an entry in the component record to show that the reason for removal was an overspeed a Main rotor yokes and blades b Main rotor mast c Transmission d Main driveshafts e Swashplate and levers assembly f Drive hub drive link and idler link assemblies g Tail rotor driveshafts h Tail rotor driveshaft hanger as...

Page 179: ...The compressor stall may cause severe torsional loading of the main driveshaft The torsional loading can cause scoring of the transmission input quill gears and damage the main driveshafts The tail rotor gearbox attach fitting may also get distorted or damaged 1 Power plant a Examine the inlet FOD screen or the particle separator if installed for blockage b Examine the compressor impeller blades f...

Page 180: ...pressor stall was the reason for removal BHT 430 CR O 2 c Remove both transmission input quills and examine the pinion gear contact patterns Use a 10X power magnifying glass to examine for scoring and other mechanical damage If damage is found return the transmission for and overhaul and make an entry in the component records that a compressor stall is the reason for removal Remove both main drive...

Page 181: ...t record to show that the reason for removal was a compressor stall or surge 5 Main rotor and blades a Visually examine the main rotor yokes and blades b Examine the blade retaining bolts and the bolts attaching the blade cuff to the adapter for deformation BHT 430 CR O c Do an inspection of the main rotor yokes and blades Make an entry in the component record to show that the reason for removal w...

Page 182: ...c Visually examine the pylon support and engine mount structures for distortion buckles cracks sheared or loose rivets d If the damage found during step a through step c cannot be repaired with standard repair procedures replace the parts as necessary CONDITIONAL INSPECTIONS 5 52 COMPRESSOR STALL OR SURGE CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Page 183: ...THIS SCHEDULE REFER TO APPLICABLE SERVICE INSTRUCTIONS FOR KIT COMPONENTS SCHEDULE NOTE Refer to paragraph 5 6 for information on inspection and overhaul tolerance NOTE Neither assignment of a time period for overhaul of a component or failure to assign a time period for overhaul of a component constitutes a warranty of any kind The only warranty applicable to helicopter and any component is that ...

Page 184: ... 103 upgrades hanger assemblies 222 044 003 109 and 111 to hanger assemblies 222 044 003 113 and 115 respectively Refer to Table 5 3 for configuration of tail rotor driveshaft hanger bearing assemblies Hanger bearings have a 3 year shelf life In addition the Royco 13 grease per MIL G 25013 also has a 3 year shelf life expiration date Expiration date is determined by adding 3 years to the manufactu...

Page 185: ...lacement only upon reaching 3000 hours of operation Bearings 222 344 606 103 must be replaced upon reaching 3 years of service regardless of the number of hours flown Bearing replacement may be accomplished without performing the complete overhaul procedure of the hanger assembly An interim inspection is necessary at 3000 hours for a new transmission and 3000 hours after each overhaul BHT 430 CR O...

Page 186: ...ing outer ring and on the seal faces Bearing must be put in service within the 3 year shelf life grease expiration date otherwise the bearing is unserviceable and must be scrapped 3 Hanger assembly P N 222 044 003 113 replaces hanger assembly P N 222 044 003 109 4 Hanger assembly P N 222 044 003 115 replaces hanger assembly P N 222 044 003 111 5 All hanger assemblies including bearing P N 222 344 ...

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BELL HELICOPTER 430, Maintenance Manual

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