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BHT-412-MM-2

5-00-00
Page 196

Rev. 26

01 JUN 2018

Export Classification C, ECCN EAR99

If the sudden stoppage conditional inspection is the
result of crash damage, all rotating system
components shall be considered unserviceable and
non-repairable. Crash damage is any damage
sustained beyond the scope of that identified in
conditional inspection (

Paragraph 5-36

)

A blade strike is due to contact of main or tail rotor
blades with the ground, water, snow, dense
vegetation or other object sufficient to cause blade
damage. However, not all blade strikes will meet the
sudden stoppage definition.

A blade strike which causes damage, dents or tear,
to a main rotor or tail rotor blade skin behind the
spar due to impact with a small foreign object (e.g.
small stone or low mass item) that did not contact
the leading edge and would not cause a sudden
deceleration of the drive system is not considered a
sudden stoppage, but may require the affected
blade(s) to be repaired.

A rotating system torque spike is defined as any
other incident which causes a severe torque spike in
the drive system. These incidents include, but are
not limited to foreign object ingestion through the
gear mesh in any gearbox.

NOTE

If overhaul evaluation is specified, complete both the
conditional inspection and normal inspection
procedures (as applicable) for that component listed
in BHT-412-CR&O.

NOTE

Components removed from a helicopter for
evaluation following a sudden stoppage shall be
evaluated as an interrelated group. Removal
records accompanying each component shall cross
reference part and serial numbers of other drive
system components removed for evaluation.

CONDITIONAL INSPECTIONS

5-38.

SUDDEN STOPPAGE — POWER ON OR OFF (CONT)

DATA REFERENCE

INSPECTION TASK DESCRIPTION

INITIAL

MECH OTHER

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Содержание Bell 412

Страница 1: ...Textron Inc and Airworthiness Directives AD issued by the applicable regulatory agencies shall be strictly followed Export Classification C ECCN EAR99 REISSUE 23 JUNE 1994 REVISION 27 25 SEPTEMBER 201...

Страница 2: ...ose other than helicopter operation or maintenance is forbidden without prior written authorization from Bell Helicopter Textron Inc Export Classification C ECCN EAR99 DESTINATION CONTROL STATEMENT WA...

Страница 3: ...S NOT APPLICABLE TO NON BELL 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 P...

Страница 4: ...E network please access http www bellflight com support and service support Model 206 505 or 407 Phone 450 437 2862 or 800 363 8023 U S Canada Fax 450 433 0272 E mail productsupport bellflight com Mod...

Страница 5: ...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 ackno...

Страница 6: ......

Страница 7: ...Manual Title Manual 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...

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

Страница 9: ..._________________________________________________ Future Publications to be mailed to this address Address ____________________________________________________________________ City ___________________...

Страница 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 T...

Страница 11: ...nd 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 ass...

Страница 12: ......

Страница 13: ...age Number Title Number Number CHAPTER 4 AIRWORTHINESS LIMITATIONS SCHEDULE AIRWORTHINESS LIMITATIONS SCHEDULE 4 1 Airworthiness Limitations Schedule 4 00 00 5 FIGURES Figure Page Number Title Number...

Страница 14: ...F SIGNATURE FAA ODA SIGNATURE Original 1 January 1981 1 15 May 1981 2 15 November 1981 3 24 February 1982 4 9 November 1982 5 9 December 1982 6 N A N A 7 31 March 1983 8 N A N A 9 N A N A 10 20 Octobe...

Страница 15: ...1990 1 20 February 1991 2 N A N A 3 N A N A Reissue N A N A 1 N A N A Reissue 23 June 1994 1 12 April 1995 2 N A N A 3 N A N A 4 N A N A 5 N A N A 6 1 October 2002 7 N A N A 8 N A N A 9 N A N A 10 N A...

Страница 16: ...2018 Export Classification C ECCN EAR99 15 1 May 2012 16 N A N A 17 26 March 2013 18 N A N A 19 N A N A 20 N A N A 21 N A N A 22 N A N A 23 N A N A 24 15 September 2016 25 N A 26 14 June 2018 27 25 SE...

Страница 17: ...ANY TIME CALENDAR RIN LIFE LIMITED COMPONENT PAST ITS STATED LIMITS IS NOT PERMITTED AS IT COULD SERIOUSLY AFFECT THE AIRWORTHINESS OF THE HELICOPTER THE COMPONENT MUST BE REMOVED FROM THE HELICOPTER...

Страница 18: ...ncluded in the Purchase Agreement for the helicopter or the component The airworthiness lives given to the components and assemblies are determined by experience tests and the judgement of Bell Helico...

Страница 19: ...18 068 101 10 000 hours or 180 months Damper Bridge 412 010 170 101 10 000 hours or 180 months Pivot Bearing 412 010 106 101 On condition Fitting 412 010 111 101 5000 hours Damper Yoke Set 412 010 145...

Страница 20: ...Ring Assembly 212 010 416 101 9000 hours Collective Sleeve 204 011 408 003 9000 hours Collective Sleeve 212 011 412 101 9000 hours Collective Lever Assembly 412 010 408 101 10 000 hours Collective Lev...

Страница 21: ...4 20 057 8 84D 2500 hours MAIN ROTOR SUPPLEMENTAL CONTROL SYSTEM BOLTS Swashplate Inner Ring to R H Cyclic Boost 1 20 057 5 24D 2500 hours Swashplate Inner Ring to L H Cyclic Boost 1 20 057 5 24D 250...

Страница 22: ...IN Cap Retention 412 010 161 101 10 000 hours Cap Retention 412 010 171 101 10 000 hours Cap Retention 412 010 171 103 10 000 hours Mast Cap 412 010 171 105 5 000 hours Cone 412 010 165 101 10 000 hou...

Страница 23: ...0 hours Cone 412 010 179 105 10 000 hours Cone 412 010 179 107 5 000 hours Lower Cone Seat 412 010 168 105 10 000 hours Lower Cone Seat 412 010 178 101 10 000 hours Lower Cone Seat 412 010 056 101 2 5...

Страница 24: ...P N 804944 209 062 908 017 6 years total life W Kidde and Co P N 895408 1 209 062 908 113 10 years total life W Kidde and Co P N 895409 1 209 062 908 115 10 years total life FLOATS Float Hose 70 072M0...

Страница 25: ...ngly When the maximum RIN or retirement flight hours is are reached whichever occurs first the component will be removed from service Refer to Information Letter GEN 94 54 Information Letter GEN 03 94...

Страница 26: ...nt dash numbers Deleted Replacement bearing cartridges 412 310 400 107 are on condition Refer to IL 412 IL 03 49 As per ASB 412 02 110 bolt 204 011 463 001 is replaced by 204 011 463 109 29022968 cont...

Страница 27: ...th AD 2000 18 09 procedures For manual tracking increase the event count by 1 for each takeoff recorded Part manufactured and part number assigned by AAI of Bristol Tennessee Retire part when event 12...

Страница 28: ...BHT 412 MM 2 FAA APPROVED 4 00 00 Page 16 Rev 24 15 SEP 2016 Export Classification C ECCN EAR99 Figure 4 1 Longitudinal Lateral CG Envelope for Hoist Operations...

Страница 29: ...15 Between 1 and 5 Flight Hours After Main Rotor Hub Installation 5 00 00 113 5 15A Between 1 and 25 Flight Hours After Expandable Blade Bolt Installation 5 00 00 114A 5 16 Between 5 and 10 Hours of...

Страница 30: ...PECTIONS 5 36 Conditional Inspection 5 00 00 187 5 37 After Hard Landing 5 00 00 189 5 38 Sudden Stoppage Power On or Off 5 00 00 195 5 39 After Overspeed 5 00 00 203 5 40 After Overtorque 5 00 00 207...

Страница 31: ...BHT 412 MM 2 5 00 00 Export Classification C ECCN EAR99 TABLES Table Page Number Title Number 5 1 Component Overhaul Schedule 234 2 SEP 2014 Rev 20 Page 2A 2B...

Страница 32: ......

Страница 33: ...ed on the Part A inspection program and it is desired to change to the Part B inspection program a complete Part A 1000 hour inspection shall be accomplished The helicopter may then be changed to the...

Страница 34: ...the scheduled inspections the special inspections and the required tests for all of the installed kits are complied with 4 Make sure all parts and components for which Historical Service Records are r...

Страница 35: ...al event known or suspected malfunctions or defects d An interim inspection occurs between overhauls e The component overhaul schedule gives the elapsed operating time at which a component must be rem...

Страница 36: ...r time Planned event Occurrence of interval in which a specific action is to be taken as in the case of preventive maintenance scheduled overhaul or replacement in accordance with maximum airworthines...

Страница 37: ...0 Hours within 10 tolerance 4050 Hours 4050 Hours 10 of 300 hours 30 hours 4050 Hours tolerance not applied 4350 Hours Calendar Example 10 or up to a maximum of 30 days calendar time whichever is less...

Страница 38: ...11 within 30 day calendar tolerance 11 000 Hours January 31 2016 11 000 Hours January 31 2016 10 of 5000 hours 500 hours maximum allowed is 100 hours or 10 of 60 months 6 months maximum allowed is 30...

Страница 39: ...NS 5 4 SCHEDULED INSPECTIONS Part A Inspect helicopter daily each 100 hours 12 months each 1000 hours each 5000 hours 5 years Part B Inspect helicopter each 25 hours 30 days each 300 hours 12 months e...

Страница 40: ......

Страница 41: ...ection program accomplish the following checks daily before flight operation GENERAL 1 Each listed inspection item or maintenance function is to be performed in accordance with the BHT 412 MM chapter...

Страница 42: ...system components wiring ducts supports and structure for damage and corrosion 2 Visually inspect overhead ventilating system components for condition and security 3 Visually inspect heat vent air du...

Страница 43: ...ystem 1 and 2 filter bypass indicator buttons not extended b Collective and cyclic servoactuators and boost tubes for leaks damage and security c Hydraulic system 1 and 2 pumps for leaks damage and se...

Страница 44: ...e surface Repair weld beads as required e Fuselage supports for wear damage and security of attachment f Deleted g If installed landing gear forward crosstube crew step fittings for corrosion damage a...

Страница 45: ...ELAGE 1 Visually inspect fuselage exterior for condition and damage to protective finish 2 Visually inspect fuselage underside for evidence of fuel and hydraulic fluid leakage 3 Visually inspect all c...

Страница 46: ...TOR HUB 1 Visually inspect main rotor hub assembly for condition and security paying particular attention to the condition of elastomeric components and the integrity of sealing 2 Visually inspect pit...

Страница 47: ...IGHT 2 Visually inspect main driveshaft forward and aft couplings boots seals and surrounding area for grease leakage damage corrosion and evidence of overheat as indicated by TEMP PLATES or coupling...

Страница 48: ...boots for condition WARNING CAUSE OF ANY DISCOLORATION SHALL BE DETERMINED AND CORRECTED PRIOR TO NEXT FLIGHT 8 Visually inspect transmission tail rotor output quill coupling and surrounding area for...

Страница 49: ...mage 3 Visually inspect oil cooler blowers for damage and obstruction Chapter 64 TAIL ROTOR HUB AND BLADE ASSEMBLY WARNING NO CRACKS ARE PERMITTED ON ANY SURFACE OF THE TAIL ROTOR BLADES 1 Tail rotor...

Страница 50: ...3 and 36001 through 36019 not modified by 412 570 001 003 or Pre BHT 412 SI 74 412SP to 412HP Upgrade WARNING CAUSE OF ANY DISCOLORATION SHALL BE DETERMINED AND CORRECTED PRIOR TO NEXT FLIGHT 1 Hanger...

Страница 51: ...cement of both outer and inner couplings step 5 5 Overheat TEMP PLATES for condition and security TEMP PLATES must not show evidence of over temperature indication deterioration debonding or excessive...

Страница 52: ...ect installation of bolts and washers WARNING CAUSE OF ANY DISCOLORATION SHALL BE DETERMINED AND CORRECTED PRIOR TO NEXT FLIGHT 9 Coupling assembly at first hanger and adjacent to transmission and sur...

Страница 53: ...coloration A change in color of one or more of the red bordered TEMP PLATE dots from white off white to black indicates an overheat condition and may require replacement of both outer and inner coupli...

Страница 54: ...condition and may require replacement of both outer and inner couplings step 7 7 Overheat TEMP PLATES for condition and security TEMP PLATES must not show evidence of over temperature indication dete...

Страница 55: ...P PLATES must not show evidence of overtemperature indication deterioration debonding or excessive discoloration of the epoxy overcoating 4 Gearbox for proper oil level and oil for evidence of contami...

Страница 56: ...oil level Chapter 71 RIGHT POWER SECTION 1 Inspect gas generator case for cracks buckled areas and hot spots 2 Inspect oil and fuel hoses and tubes for chafing leaking and security 3 Inspect electrica...

Страница 57: ...isually inspect instrument panel for cleanliness 2 Visually inspect all instruments placards decals and markings for appearance and legibility 3 Check magnetic compass for condition and security 4 Vis...

Страница 58: ...dition and security Chapter 96 BATTERY SYSTEM 1 Visually inspect battery and external connections for condition and security 2 Visually inspect battery vent and drain tubes for obstruction and securit...

Страница 59: ...inspection program accomplish each 100 hours of flight operation or after 12 calendar months whichever comes first GENERAL 1 Each listed inspection item or maintenance function is to be performed in a...

Страница 60: ...replace the filler caps or replace sealing O rings as required AFTER COMPLETION OF INSPECTION 1 Reinstall all panels fairings and cowlings removed during inspection 2 Carry out a ground run and leak c...

Страница 61: ...condition and security until Part III of referenced ASB is accomplished Chapter 96 3 Perform operational check of engine fire extinguishing system 4 Perform operational check of baggage compartment s...

Страница 62: ...500 PSI 0 to 3447 kPa gauge in quick disconnect at rotor brake caliper Slowly pull rotor brake handle through travel Cylinder should generate 240 to 260 PSI 1655 to 1793 kPa at any handle velocity an...

Страница 63: ...nspect for condition Chapter 52 DOORS AND WINDOWS 1 Crew and passenger doors structure for corrosion damage distortion and positive locking mechanisms Seals for adherence tears separations and deterio...

Страница 64: ...fitting for cracks and security 6 Cabin interior and exterior for corrosion and damage 7 All compartments for evidence of water entrapment and corrosion 8 Ensure all drain holes are open 9 Inspect und...

Страница 65: ...or damage delamination and corrosion NOTE To adequately inspect the following it will be necessary to remove the auxiliary fuel tanks if installed 2 Pylon wall for damage working fasteners cracks dela...

Страница 66: ...light and small mirror to inspect area for cracks especially near rivets holes NOTE Step 9 and step 10 pertain to helicopters modified with the BLR FastFin system kit 412 705 040 101 For helicopters e...

Страница 67: ...4 Report any cracks to Product Support Engineering 5 Install plug button with sealant C 308 Chapter 62 MAIN ROTOR BLADES 1 Wash main rotor blades 2 Inspect main rotor blades upper and lower surfaces...

Страница 68: ...s Apply a minimum of 5 pounds 22 24 N of force to each arm and bearing assembly force toward center of yoke Cycle arm and bearing through full travel 8 Apply force away from center of yoke Arm and bea...

Страница 69: ...ks spherical bearings shall not exceed 0 007 inch 0 178 mm radial or 0 015 inch 0 381 mm axial looseness d Swashplate link non elastomeric bearing looseness shall not exceed 0 015 inch 0 381 mm axial...

Страница 70: ...MAST 1 Inspect mast assembly for security corrosion and mechanical damage 2 Inspect mast torque sensor if installed installation for security and condition 3 Inspect for evidence of oil leaks at mast...

Страница 71: ...OULD CAUSE MECHANICAL FAILURE RESULTING IN EXCESSIVE VIBRATION OR DAMAGE TO THE TAIL ROTOR BLADES 1 Inspect the tail rotor counterweight bellcrank 212 011 705 001 retention nuts for cracks corrosion a...

Страница 72: ...6999 S N 37002 through 37999 S N 38001 through 38999 S N 39101 through 39999 and helicopters modified by 412 570 001 103 or Post BHT 412 SI 74 412SP to 412HP Upgrade check disc pack couplings and atta...

Страница 73: ...exposed area of actuator piston with hydraulic fluid C 002 or hydraulic fluid C 072 and lint free cloth j Check cyclic and collective hydraulic cylinders piston rods for evidence of excessive wear and...

Страница 74: ...skin and corrosion d Inspect trailing edge tabs and tip caps for condition and security e Functionally check operation of control tube as follows CAUTION DO NOT RELEASE ELEVATOR AND ALLOW THE SPRING T...

Страница 75: ...tubes for damage chafing corrosion and security of attachment b Check cyclic stick friction adjuster for proper operation c Check for proper cyclic minimum friction d Check cyclic flight controls for...

Страница 76: ...ter 71 POWER PLANT Every third 100 hour inspection 300 hours or 12 months NOTE Refer to the applicable Pratt Whitney Canada Engine Maintenance Manual for engine inspection requirements 1 No 1 left eng...

Страница 77: ...and security d Power section 2 starter generator cooling ducts for obstruction kinking and security 6 Engine fire detection system elements for condition and security NOTE If applicable refer to BHT 4...

Страница 78: ...ntenance Manual 1 Perform maximum NG topping check Chapter 96 ELECTRICAL SYSTEM 1 Check inverters for security of mounting and connections 2 Check generator control units for damage and security of mo...

Страница 79: ...light Chapter 96 EMERGENCY BUS AND POWER DIODES Every third 100 hour inspection 300 hours or every 12 months 1 Perform operational check of emergency bus system as follows NOTE Helicopters S N 33001 t...

Страница 80: ...dles illuminate Verify INVERTER 1 and INVERTER 2 segments are illuminated on the caution panel NOTE S N 33108 through 33213 and 36001 through 36999 Check INVERTER 1 light segment on the caution panel...

Страница 81: ...Part A inspection program accomplish each 1000 hours of flight operation GENERAL 1 Each listed inspection item or maintenance function is to be performed in accordance with the BHT 412 MM chapter spe...

Страница 82: ...013 Export Classification C ECCN EAR99 5 Reconnect drive and swashplate links and tubes and drive plate set to hub assembly SCHEDULED INSPECTIONS 5 7 1000 HOUR INSPECTION PART A CONT DATA REFERENCE IN...

Страница 83: ..._____________ NOTE For helicopters on the Part A inspection program accomplish each 5000 hours flight time or 60 months whichever comes first This inspection is meant to be a full visual inspection of...

Страница 84: ...complete inspection of the landing gear attachment points and support structure 4 In addition to the 5000 Hour 5 Year Inspection Part A items carry out the following a Complete Daily Inspection Part A...

Страница 85: ...damage corrosion and cracking 5 Right and left BL 14 00 main beams forward of STA 23 00 for damage corrosion and cracking 6 Instrument panel attachment structure for damage corrosion and cracking pri...

Страница 86: ...ication of wear at attaching points 20 Crew seat support beams at BL 14 00 and 30 00 between FS 23 00 and 74 30 for cracks and corrosion 21 Forward crosstube attachment points and support structure at...

Страница 87: ...oints for corrosion Access panels and covers for condition and attachment 27 Main transmission compartment interior FS 129 00 to 166 00 and WL 7 44 to 76 00 for corrosion Bulkheads and main beam panel...

Страница 88: ...BL 50 00 left and right side for damaged skin and joints for corrosion bonded panels for disbonding and corrosion Structure above overhead console circuit breaker panels for cracks and corrosion 37 Ca...

Страница 89: ...or bulkheads and stringers for cracks and corrosion 8 Intermediate gearbox mount pad for damage cracks fretting and corrosion 9 Tail rotor gearbox support fitting assembly for damage cracks fretting a...

Страница 90: ...cracks using a 3X magnifying glass and a bright light Pay particular attention to the base of the throttle slots that form the twist grip stops 3 If a crack is found replace stick tube 4 Reassemble pi...

Страница 91: ...00 00 Export Classification C ECCN EAR99 Figure 5 1 Collective Stick Tube Part A 412_MM_05_0002 UPPER THROTTLE SLOT STICK TUBE AREA TO BE INSPECTED AREA TO BE INSPECTED LOWER THROTTLE SLOT 2 SEP 2014...

Страница 92: ...n C ECCN EAR99 5 00 00 Figure 5 1A Cabin Frame Inspection Part A 412_MM_05_0004 1 3 4 5 2 A VIEW A 1 2 3 4 5 Outboard cabin post Sticker plate aft Cabin roof longeron Sticker plate forward Windshield...

Страница 93: ...accomplish the following checks each 25 hours of flight operation or 30 days whichever occurs first GENERAL 1 Each listed inspection item or maintenance function is to be performed in accordance with...

Страница 94: ...ent and for missing or damaged twist fasteners seal for condition Chapter 53 3 Fuselage a Forward fuselage area structure and skin for damage corrosion cleanliness and damage to protective finish b Av...

Страница 95: ...elage underside for evidence of fuel and hydraulic fluid leakage Chapter 28 3 Visually inspect fuel samples for contamination Chapter 32 4 Landing gear a Forward crosstube and cap fittings for conditi...

Страница 96: ...enger cargo doors and surrounding structure for damage corrosion and proper operation Window seals for condition Chapter 25 8 Crew seats a Seats for condition security and proper operation b Cushions...

Страница 97: ...ghts and map lights for serviceability d All caution and warning lights for proper operation by using master caution fire test and baggage compartment smoke detector press to test functions e Landing...

Страница 98: ...nd hoses for condition damage chafing and leaks paying particular attention to lines running aft of the thermostatic relief valve f Transmission mount dust boots for condition WARNING CAUSE OF ANY DIS...

Страница 99: ...king and security 17 Flight control tubes for condition corrosion and security FUSELAGE AFT OF CABIN LEFT AND RIGHT SIDE Chapter 52 1 Avionics electrical and heater compartment doors for condition and...

Страница 100: ...r leakage corrosion damage and obstruction b Oil cooler hoses and tubes for leakage damage chafing and fraying c Reduction gearbox oil filter impending bypass indicator button not extended d Power sec...

Страница 101: ...m for cracks distortion missing rivets broken spot welds and deteriorating seals or gaskets Chapter 71 14 Engine cowling for missing fasteners and cracks Latches for proper operation Chapter 53 FUSELA...

Страница 102: ...splices longerons attach fittings and hardware for condition corrosion damage and cracks NOTE Step c and step d pertain to helicopters modified with the BLR FastFin system kit 412 705 040 101 For hel...

Страница 103: ...6 Nm If any nut rotates under torque inspect attachment hardware and tail rotor gearbox for serviceability i Torque check intermediate gearbox mounting bolts by applying torque in tightening directio...

Страница 104: ...HT d Flexible couplings and surrounding areas for grease leakage damage corrosion and evidence of overheat as indicated by TEMP PLATES or coupling discoloration A change in color of one or more of the...

Страница 105: ...e distortion dents corrosion and for damage to anodized finish c Disc pack couplings for separation deflection distortion cracks or missing sections and correct installation of bolts and washers WARNI...

Страница 106: ...ND CORRECTED PRIOR TO NEXT FLIGHT b Input and output quill flexible couplings and surrounding area for grease leakage damage corrosion and evidence of overheat as indicated by TEMP PLATES or coupling...

Страница 107: ...verheat as indicated by TEMP PLATES or coupling discoloration A change in color of one or more of the red bordered TEMP PLATE dots from white off white to black indicates an overheat condition and may...

Страница 108: ...may require replacement of both outer and inner couplings step c c Overheat TEMP PLATES for condition and security TEMP PLATES must not show evidence of over temperature indication deterioration debo...

Страница 109: ...cessive looseness and freedom of movement through full range of travel with antitorque pedals positioned full right and then full left d Tail rotor pitch change links crosshead pitch horns counterweig...

Страница 110: ...rrosion and security Reapply corrosion preventive compound C 101 if nuts are not completely covered CABIN ROOF Chapter 52 Chapter 53 1 Cabin structure and cowlings fairings for condition Chapter 63 2...

Страница 111: ...ing b Inspect pitch horns for condition security and corrosion and cracks in areas surrounding torque transfer pin holes No cracks permitted c Inspect pivot bearings spindle bearings and damper set fo...

Страница 112: ...and drive link bearings workaid Chapter 62 to assist with determining condition of main rotor control bearings c Visually inspect drive hub and rephasing levers for bearing looseness and security of a...

Страница 113: ...ot exceed 0 007 inch 0 178 mm radial or 0 015 inch 0 381 mm axial looseness f Swashplate link non elastomeric bearing looseness shall not exceed 0 015 inch 0 381 mm axial g Collective lever trunnion b...

Страница 114: ...ATE from white off white to black will indicate a possible overheat condition and or component degradation step c If one or more of the red bordered TEMP PLATE dots change from white off white to blac...

Страница 115: ..._______ NOTE For helicopters on the Part B inspection program accomplish the following checks each 300 hours of flight operation or 12 calendar months whichever occurs first GENERAL Each listed inspec...

Страница 116: ...or condition and security Perform operational check c Passenger door structure for corrosion damage distortion and positive locking mechanisms d Nose electrical and equipment compartment access doors...

Страница 117: ...attaching actuator to lower supports Check cylinder alignment to lower support Rod end bearing side loads are not permitted Install bolts k Torque check nuts attaching actuator cylinder to upper supp...

Страница 118: ...and requires adjustment j Remove bolts attaching actuator to lower supports Check cylinder alignment to lower support Rod end bearing side loads are not permitted Install bolts k Torque check nuts at...

Страница 119: ...Bearings for looseness i Mast torque sensor if installed installation for condition and security BHT 412 CR O j Torque check top case to ring gear case nuts ring gear case to main case nuts and main c...

Страница 120: ...Fuselage structure for damage corrosion and working rivets b Exterior finish for condition and cleanliness c Evidence of excessive fluid leakage d Structure around landing gear for condition e Forward...

Страница 121: ...urity b Power section 2 ignition leads for corrosion chafing and security Chapter 71 5 Starter generator a Power section 1 starter generator brushes for allowable wear b Power section 2 starter genera...

Страница 122: ...on and security TAILBOOM Chapter 53 1 Tailboom structure a Tailboom exterior structure for corrosion and damage b Tailboom interior structure for corrosion and damage c Inspect tailboom joints splices...

Страница 123: ...l tubes between tail rotor pedals and tail rotor gearbox for corrosion wear and damage b Control tube bellcranks supports and attaching hardware for corrosion security wear and damage c Tail rotor hyd...

Страница 124: ...tall elevator control tube g Functionally check elevator rigging for proper setting and travel h Inspect and measure elevator trailing edge tab for 16 1 4 angle down from upper surface of elevator Cha...

Страница 125: ...ers modified by 412 570 001 103 or Post BHT 412 SI 74 412SP to 412HP Upgrade Chapter 65 8 Tail rotor driveshaft a Hanger assemblies for cracks at mounting ears corrosion and security of attachment b H...

Страница 126: ...rotor blade retention bolts c Torque check tail rotor retaining nut CABIN ROOF Chapter 52 Chapter 53 1 Cabin roof structure a Cabin roof structure cowlings and fairings for damage delamination and gen...

Страница 127: ...four hub and sleeve to rephasing lever attachment bolts to 24 to 34 foot pounds 33 to 46 Nm for 1 2 inch bolts or to 160 to 200 inch pounds 18 08 to 22 59 Nm for 3 8 inch bolts if installed d Torque...

Страница 128: ...RG LOAD position Check emergency bus power by pressing the FIRE EXT PRESS TO TEST button momentarily Observe both FIRE PULL handles illuminate Verify INVERTER 1 and INVERTER 2 segments are illuminated...

Страница 129: ...___________ _________________________ NOTE For helicopters on the Part B inspection program accomplish the following checks each 600 hours of flight operation or 12 calendar months whichever occurs fi...

Страница 130: ...Chapter 52 3 Perform operational check of crew doors emergency release mechanisms Chapter 21 Chapter 96 4 Bleed air heating and ventilation defog system components a Perform functional check of bleed...

Страница 131: ...s for damage chafing corrosion and security of attachment b Check cyclic stick friction adjuster for proper operation c Check for proper cyclic minimum friction d Check cyclic flight controls for smoo...

Страница 132: ...007 elements are interchangeable intermixing of different element types is not permitted a Remove and inspect hydraulic filter elements b Discard or clean filter elements as applicable c Install hydr...

Страница 133: ...steners cracks delamination and corrosion Chapter 96 15 Electrical system a Check inverters for security of mounting and connections b Check generator control units for damage and security of mounting...

Страница 134: ...washplate and support assembly hub and sleeve assembly a Disconnect drive and swashplate links from swashplate outer ring b Disconnect pitch links from main rotor hub pitch horns c Disconnect the coll...

Страница 135: ...Type Certificate STC refer to the applicable BLR Aerospace documents for inspection criteria 2 Inspect upper and lower tail fairings for visible damage to the exterior skin and cracks at the attachme...

Страница 136: ...f horn where control tube is normally installed Pull scale at right angle to arm verify friction is 26 to 32 pounds 115 65 to 142 34 N If friction is not within limits adjust shim thickness e Install...

Страница 137: ...___ NOTE For helicopters on the Part B inspection program accomplish the following checks each 5000 hours flight time or 60 months whichever occurs first This inspection is meant to be a full visual i...

Страница 138: ...mplete inspection of the landing gear attachment points and support structure 4 In addition to the 5000 Hour 5 Year Inspection Part B items do the following a Complete 25 Hour 30 Day Inspection Part B...

Страница 139: ...damage corrosion and cracking 5 Right and left BL 14 00 main beams forward of STA 23 00 for damage corrosion and cracking 6 Instrument panel attachment structure for damage corrosion and cracking pri...

Страница 140: ...dication of wear at attaching points 20 Crew seat support beams at BL 14 00 and 30 00 between FS 23 00 and 74 30 for cracks and corrosion 21 Forward crosstube attachment points and support structure a...

Страница 141: ...nts for corrosion Access panels and covers for condition and attachment 27 Main transmission compartment interior FS 129 00 to 166 00 and WL 7 44 to 76 00 for corrosion Bulkheads and main beam panels...

Страница 142: ...BL 50 00 left and right side for damaged skin and joints for corrosion bonded panels for disbonding and corrosion Structure above overhead console circuit breaker panels for cracks and corrosion 37 Ca...

Страница 143: ...e cracks fretting and corrosion 9 Tail rotor gearbox support fitting assembly for damage cracks fretting and corrosion Pay particular attention to mounting holes and lugs 10 Tailboom exterior bonded p...

Страница 144: ...the throttle slots that form the twist grip stops 3 If a crack is found replace stick tube 4 Reassemble pilot and copilot if applicable collective stick s 5 Check throttle controls for proper operatio...

Страница 145: ...0 00 Export Classification C ECCN EAR99 Figure 5 2 Collective Stick Tube Part B 412_MM_05_0002 UPPER THROTTLE SLOT STICK TUBE AREA TO BE INSPECTED AREA TO BE INSPECTED LOWER THROTTLE SLOT 2 SEP 2014 R...

Страница 146: ...n C ECCN EAR99 5 00 00 Figure 5 2A Cabin Frame Inspection Part B 412_MM_05_0004 1 3 4 5 2 A VIEW A 1 2 3 4 5 Outboard cabin post Sticker plate aft Cabin roof longeron Sticker plate forward Windshield...

Страница 147: ...h 2500 hours of main rotor hub assembly operation Each 2500 hours of main rotor blade operation Each 2500 or 3000 hours of main rotor mast 412 040 366 109 and subsequent operation Each 2500 hours of t...

Страница 148: ...additional information refer to the BHT ALL SPM If any confusion exists or a clarification is desired contact Product Support Engineering MANUAL SPECIFIES SUGGESTED TIME FRAME TO ACCOMPLISH 100 hours...

Страница 149: ...AL BEVEL GEAR 204 040 701 103 ASB 412 89 42 Affected helicopter S N 33001 through 33138 33150 through 33160 33168 through 33175 33177 33178 33179 33181 33182 33185 33186 and 33192 Spare uninstalled sp...

Страница 150: ...A 124 A 125 A 127 A 128 A 129 A 132 A 133 A 140 Model 412 33175 33177 33178 33179 33181 33182 33185 33186 SPARE 33192 Chapter 63 BHT 412 CR O 1 Remove and inspect transmission internal sump filter for...

Страница 151: ...tal time of any gear replaced d Install quill pad cover or rotor brake quill 3 Return spare uninstalled affected serial numbered spiral bevel gears to Bell Helicopter Textron for inspection and re ide...

Страница 152: ......

Страница 153: ..._______________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish between 1 and 5 hours of flight after installation of main rotor...

Страница 154: ......

Страница 155: ...Figure 5 4A force at initial installation and again in 1 to 25 flight hours after installation Chapter 62 EXPANDABLE BLADE BOLT 412 010 137 103 1 Remove safety lock pin from lower end of expandable b...

Страница 156: ......

Страница 157: ...______________ NOTE Accomplish between 5 and 10 hours of flight after each installation Chapter 64 TAIL ROTOR HUB AND BLADE ASSEMBLY 1 Torque check tail rotor hub retaining nut to 900 inch pounds 101...

Страница 158: ......

Страница 159: ...AIL ROTOR HANGER BEARINGS WITNESS MARKS ASB 412 95 84 Revision C 1 Perform helicopter run up for 5 minutes Shut down helicopter and inspect tail rotor hanger bearings for movement of the dust shields...

Страница 160: ......

Страница 161: ...212 011 713 Tail rotor static stop 212 011 713 for straightness across the outboard surface If yielding has occurred replace the tail rotor yoke and static stop If any doubt exists as to the serviceab...

Страница 162: ...equires the blade be removed from service 5 Only superficial corrosion that can be removed with aluminum wool or very fine grade abrasive pad C 407 is permissible Corrosion on the spar 0 003 inch deep...

Страница 163: ...Export Classification C ECCN EAR99 Figure 5 3 Tail Rotor Blade Special Inspection 412_MM_05_0003 STA 5 00 STA 51 00 STA 20 00 STA 35 00 10X MAGNIFICATION 3X MAGNIFICATION 3X MAGNIFICATION 26 FEB 2013...

Страница 164: ......

Страница 165: ...____________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish 50 flight hours after each installation of components Chapte...

Страница 166: ......

Страница 167: ...__________ FACILITY _________________ _________________________ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME ______________________...

Страница 168: ......

Страница 169: ...e lever 412 010 408 101 and 105 operation COLLECTIVE LEVER 412 010 408 101 105 1 Prepare helicopter for maintenance a Gain access to the collective lever 2 Use cleaning compound C 318 or equivalent to...

Страница 170: ...he collective lever with a serviceable part and contact Product Support Engineering to report the defect 7 If no cracks are found refinish as required per the BHT 412 CR O Manual SPECIAL INSPECTIONS 5...

Страница 171: ...BHT 412 MM 2 5 00 00 Export Classification C ECCN EAR99 Figure 5 4 Collective Lever Special Inspection 26 FEB 2013 Rev 16 Page 129 130...

Страница 172: ......

Страница 173: ...______________ NOTE Accomplish each 150 hours of starter generator 200SG119Q operation or more frequently if conditions warrant Part number 200SG119Q refers to the starter generator without the QAD ki...

Страница 174: ......

Страница 175: ..._____________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 300 hours or 6 months of main rotor expandable blade bolt oper...

Страница 176: ...he BHT 412 CR O Chapter 62 5 Attach the blade bolt segment removal installation workaid to the threaded end of the core pin 5 until firmly seated finger tight only 6 Hold or secure the bolt handle 2 a...

Страница 177: ...a thin continuous layer of grease C 561 to the core pin 5 and the segments 3 both internally and externally on all surfaces 11 To begin reassembly hold the end of the blade bolt segment removal insta...

Страница 178: ...xpandable blade bolt Bolt handle Segments Nut Core pin 1 2 3 4 5 GREASE C 561 BEVEL SIDE FACING INWARDS BLADE BOLT SEGMENT REMOVAL INSTALLATION WORKAID BLADE BOLT SEGMENT REMOVAL INSTALLATION WORKAID...

Страница 179: ...NATURE _______________ _________________________ NOTE Accomplish each 600 hours of tail rotor driveshaft operation or 12 months whichever occurs first no Non Destructive Inspection NDI required Chapte...

Страница 180: ...through 38999 S N 39101 through 39999 and helicopters modified by 412 570 001 103 or Post BHT 412 SI 74 412SP to 412HP Upgrade Chapter 65 BHT 412 CR O 1 Remove tail rotor coupling assembly 412 040 601...

Страница 181: ...box NOTE Disassemble flexible coupling only to the extent necessary to remove old grease and repack 7 Clean visually inspect and repack intermediate gearbox flexible coupling 8 Install tail rotor driv...

Страница 182: ...0 hours of main driveshaft operation or 12 months whichever occurs first no Non Destructive Inspection NDI required MAIN DRIVESHAFT 212 040 005 003 007 103 AND 412 040 005 101 103 Chapter 63 BHT 412 C...

Страница 183: ...age 137 Export Classification C ECCN EAR99 Chapter 18 4 Balance driveshaft to below 0 2 IPS SPECIAL INSPECTIONS 5 24 EACH 600 HOURS OF MAIN DRIVESHAFT OPERATION OR 12 MONTHS CONT DATA REFERENCE INSPEC...

Страница 184: ...E _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 1000 hours of component operation Chapter 29 HYDRAULIC ACCUMULATORS TB 412 17 240 NOT...

Страница 185: ...blowers BHT 412 CR O 2 Disassemble clean and visually inspect for corrosion and damage 3 Replace bearings and any other unserviceable parts 4 Reassemble oil cooler blowers 5 Install oil cooler blower...

Страница 186: ...___ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 12 Months or 2500 landings whichever occurs first HIGH AFT CROSSTUBE ASS...

Страница 187: ...om the landing gear assembly 3 Remove the support beam assembly from the high aft crosstube assembly 4 Remove the hardware retaining the left and right clamp assemblies 1 Figure 5 5 on the crosstube C...

Страница 188: ...ir instructions NOTE The upper support 4 on the aft crosstube 3 is bonded with structural adhesive and is not designed to be removed Chapter 32 10 Inspect the upper support 4 for signs of looseness or...

Страница 189: ...M 16 If the fluorescent penetrant inspection is not going to be accomplished immediately then protect the crosstube by applying corrosion preventive compound C 125 Wrap exposed area in barrier materia...

Страница 190: ...Chapter 32 b Inspect crosstube for damage per limits specified in the Chapter 32 to determine allowable damage and cleanup c No cracks are permitted Chapter 32 d Repair all damage in accordance with...

Страница 191: ...ckets 22 Torque clamp assembly 1 nuts 50 to 70 inch pounds 5 6 to 7 9 Nm NOTE The T bolt should have approximately 0 5 inch 12 7 mm of threads visible after installation BHT ALL SPM 23 If required tri...

Страница 192: ...2 5 00 00 Page 146 Rev 23 15 DEC 2015 Export Classification C ECCN EAR99 Figure 5 5 Aft High Crosstube Special Inspection Sheet 1 of 2 412_MM_05_0002a 1 2 DETAIL A VIEW LOOKING FORWARD A B 2 5 IN 63 5...

Страница 193: ...ion strip Aft crosstube Upper support Larson L101 abrasion strip Lower support 3 6 4 5 0 05 TO 0 15 IN 50 TO 70 IN LBS 5 6 TO 7 9 Nm T DETAIL B VIEW LOOKING FORWARD 1 2 3 Remove paint primer from the...

Страница 194: ...________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ ________________________ NOTE Accomplish each 24 months of control bolt operation FLIGHT CONTROL S...

Страница 195: ...d corrosion Replace any bolt that has damaged threads detectable shank wear or exhibits corrosion pitting 4 Apply corrosion preventive compound C 104 to bolt shanks only and install Do not apply to th...

Страница 196: ...owing quantities apply a Drive link to rephasing lever 2 20 057 36D b Swashplate link to rephasing lever 3 20 057 6 38D c Swashplate link to rotating ring 3 20 057 6 36D As per ASB 412 98 92 bolt 20 0...

Страница 197: ..._______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish every 24 months of main rotor mast operation when operating in a non corrosive environment...

Страница 198: ......

Страница 199: ...sh each 2500 hours of main rotor hub operation MAIN ROTOR HUB ASSEMBLY 412 010 100 SERIES AND 412 010 502 SERIES Chapter 62 BHT 412 CR O 1 Disassemble main rotor hub Visually inspect eight drive pins...

Страница 200: ...replace droop restraint bolts if any thread damage shank wear distortion or corrosion is detected 5 Visually inspect simple pendulum absorbers components for condition and security Inspect and replac...

Страница 201: ...___ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ ________________...

Страница 202: ......

Страница 203: ...__ SIGNATURE _______________ _________________________ NOTE Accomplish each 2500 hours of main rotor mast 412 040 366 109 and subsequent operation on helicopters S N 36020 through 36670 and helicopter...

Страница 204: ...spections The mast assembly must be returned with torquemeter tube plug and lower torquemeter rotor in place Also note the number of the monopole sensor 412 375 004 105 or 107 used with the mast 1 Rem...

Страница 205: ...bearing nut 412 040 104 101 or 412 040 104 103 by applying torque in increasing torque direction Do not exceed 1400 foot pounds 1898 Nm for 101 nut or 900 foot pounds 1220 Nm for 103 nut NOTE It may...

Страница 206: ...used for the spline teeth depends on the serial number of the mast assembly and the part number of the monopole sensor used with the mast assembly b For mast assemblies 412 040 366 111 and subsequent...

Страница 207: ...______ NOTE Accomplish each 2500 hours of tail rotor drive system operation on helicopters S N 36020 through 36999 S N 37002 through 37999 S N 38001 through 38999 S N 39101 through 39999 and helicopte...

Страница 208: ...ence of fretting wear and or corrosion 5 Visually examine coupling 412 340 610 laminations for evidence of wear and or corrosion 6 After intermediate gearbox tail rotor gearbox and hanger assemblies h...

Страница 209: ...torque verification remove bolt 204 040 612 d Remove outer coupling and inner crown tooth coupling e Remove inner coupling from outer coupling Remove retainer 214 040 633 427 044 121 seal 214 040 812...

Страница 210: ...ures and wear and damage limits BHT 412 CR O 2 Clean external surfaces of hanger assembly 3 Visually inspect hanger assembly as follows a Inspect hanger for evidence of wear dents enlarged mounting sl...

Страница 211: ...or disassembly cleaning assembly inspection procedures and wear and damage limits BHT 412 CR O 3 Clean external surfaces of coupling assembly 4 Visually inspect coupling assembly as follows WARNING CA...

Страница 212: ...ling from outer coupling Remove retaining ring Remove retainer seal and housing from female coupling as an assembly Using an arbor press ensure retainer is fully seated in housing e Remove sleeve from...

Страница 213: ...nd adjacent area surfaces for evidence of grease leakage 2 Remove coupling assembly from helicopter NOTE Refer to the BHT 412 CR O for disassembly cleaning assembly inspection procedures and wear and...

Страница 214: ...While holding end plate against spring remove retaining ring Remove end plate and spring Visually examine end plate spring and retaining ring for evidence of wear and or corrosion b Remove cotter pin...

Страница 215: ...ed teeth h Inspect end plate for damage that could cause leakage of lubricant i Inspect seal in place for distortions cuts tears and deterioration j Inspect seal housing for damage that could cause le...

Страница 216: ...r Check torque of bolt using increasing torque Do not exceed 80 foot pounds 108 Nm If bolt turns under torque inspect for serviceability 3 Install input quill adapter retainer and spring lock SPECIAL...

Страница 217: ...________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 3000 hours of main rotor mast 412 040 366 103 and 105 operation on helicopters S N 33001 throu...

Страница 218: ...es on mast for dents wear or damage 8 Check torque on upper mast bearing nut 412 040 104 101 or 412 040 101 103 by applying torque in increasing torque direction Do not exceed 1400 foot pounds 1898 Nm...

Страница 219: ...nt of the damage 10 Visually examine inside and outside exposed surfaces of mast pole assembly for evidence of corrosion and or mechanical damage 11 Assemble main rotor mast assembly SPECIAL INSPECTIO...

Страница 220: ......

Страница 221: ...________ NOTE Accomplish each 3000 hours of transmission 412 040 002 operation on helicopters S N 33001 through 33213 and S N 36001 through 36019 not modified by 412 570 001 103 or BHT 412 SI 74 412SP...

Страница 222: ...een pinion teeth and main case NOTE If index marks indicate rotational movement between pinion and inner race of bearing set remove quill and bearing set and inspect pinion bearing journal for signs o...

Страница 223: ...OF ANY FORM OF LUBRICANT TO FACILITATE INSTALLATION OF GEAR ON SHAFT WILL RESULT IN TORQUE LOSS OF ATTACHMENT BOLTS AND SUBSEQUENT FRETTING DAMAGE NOTE During assembly of spiral bevel gear to shaft en...

Страница 224: ......

Страница 225: ...icopters S N 36020 through 36999 S N 37002 through 37999 and helicopters modified by 412 570 001 103 or Post BHT 412 SI 74 412SP to 412HP Upgrade Chapter 63 BHT 412 CR O MAIN TRANSMISSION 412 040 004...

Страница 226: ...om of sump case Visually inspect detectors for cut packings burrs bent tubes and foreign material Clean detectors as required with MEK C 309 7 Any foreign material found on detectors or in lubricant s...

Страница 227: ...257 as an assembly Do not disassemble h Remove lower sun gear 205 040 229 BHT 412 CR O 10 Planetary component inspection a Visually inspect all parts of planetary assembly for evidence of wear and or...

Страница 228: ...freedom from binding by rotating the four pinion assemblies Visually inspect all lockwire provisions h Visually inspect lower sun gear 205 040 229 teeth for wear damage and contact pattern 11 Check ba...

Страница 229: ...or excessive wear scoring pitting and contact pattern Visually inspect vibro etched index marks on pinion 412 040 700 and bearing set 214 040 118 for alignment Inspection may be accomplished with inpu...

Страница 230: ...move adapter 212 040 206 Inspect both splines for evidence of damage and or wear c Check installation of cotter pin six places d Visually inspect for proper installation of retainer e Visually inspect...

Страница 231: ...Remove oil pump and visually examine spline for general condition Rotate pump by hand and check for freedom of rotation h Remove accessory quill hydraulic and tach drive Visually examine pilot diamet...

Страница 232: ......

Страница 233: ...eam cap 205 030 186 005 installed accomplish at 3600 hours total airframe time and each 300 hours or 12 months thereafter whichever occurs first If main beam cap 205 030 186 005 has been replaced use...

Страница 234: ......

Страница 235: ...rike or other rotating system torque spike overspeed overtorque compressor stall or surge lightning strike and after engine combining gearbox clutch non engagement misengagement or in flight slippage...

Страница 236: ......

Страница 237: ...component records of each component removed to cross reference part and serial numbers of other drive system components removed for evaluation Hard landing is defined as any accident or incident in w...

Страница 238: ...Inspect tailboom and fuselage attachment for loose rivets cracks or other damage g If no damage other than yielded landing gear crosstubes has been found at this point a true hard landing probably did...

Страница 239: ...thorough visual inspection of the following components that may be kept in service if no discrepancy or obvious damage is found Replace any damaged component 1 Main rotor blades 2 Main rotor hub 3 Ta...

Страница 240: ...upport structure for loose or sheared rivets cracked brackets buckled or cracked support angles and webs Pay particular attention to pylon mounts attaching points e Make a complete inspection of lift...

Страница 241: ...supports and for damaged control system bearings Pay particular attention to pylon controls lower cylinder attachment support fitting and adjacent airframe structure Chapter 29 l Pressurize hydraulic...

Страница 242: ......

Страница 243: ...nal inspection does not fully reflect the occurrence or if additional information or clarification is required please contact Product Support Engineering for assistance NOTE Sudden stoppage conditiona...

Страница 244: ...contact the leading edge and would not cause a sudden deceleration of the drive system is not considered a sudden stoppage but may require the affected blade s to be repaired A rotating system torque...

Страница 245: ...oppage Refer to BHT 412 CR O for repair limits 3 Blades may remain in service if no damage was found or if damage was within acceptable damage limits b Main Rotor Hub and Pylon Controls 1 If main roto...

Страница 246: ...udden stoppage 4 Perform Main Driveshaft Conditional inspection in accordance with BHT 412 CR O d Transmission and mast assembly 1 If a sudden stoppage incident was confirmed as a Result of impact dam...

Страница 247: ...nsidered scrap and transmission assembly shall have an overhaul evaluation performed Make an entry in the component records to show the reason for removal is sudden stoppage c Remove transmission top...

Страница 248: ...Make an entry in the component records to show reason for removal is sudden stoppage a Tail rotor gearbox assembly If during the overhaul cracks sheared or bend studs or evidence of case distortion a...

Страница 249: ...entry in the component records to show reason for removal is a sudden stoppage 4 If the inspection is being conducted as a result of a tail rotor driveshaft intermediate gearbox or tail rotor gearbox...

Страница 250: ...lies and shafts shall be overhauled Make an entry in the components records to show reason for removal is a sudden stoppage 3 If any driveshafts fails because of torsional overload remove and scrap al...

Страница 251: ...rivets or damage 2 Inspect tail rotor driveshaft support structure for cracks shear rivets or damage e Transmission sump assembly NOTE If transmission assembly has already been removed for overhaul om...

Страница 252: ...med Make an entry in component record to show reason for removal was blade strike or torque spike 3 Install or replace as applicable all removed components with like serviceable components 4 Refer to...

Страница 253: ...ts removed from a helicopter for evaluation following an overspeed shall be evaluated as an interrelated group Removal records accompanying each component shall cross reference part and serial numbers...

Страница 254: ...b and blade assembly 2 Remove tail rotor blades 3 Replace tail rotor blade retention bolts d Tail rotor blades BHT 412 CR O 1 Perform Major Overspeed Inspection of tail rotor blades 2 Make an entry in...

Страница 255: ...ade assembly Install serviceable tail rotor blades Balance and install tail rotor hub and blade assembly Pratt Whitney Canada Engine Maintenance Manual g Refer to applicable Pratt Whitney Canada Engin...

Страница 256: ......

Страница 257: ...licopter for evaluation following an overtorque shall be evaluated as an interrelated group Make entries in component records to cross reference part and serial numbers of other drive system component...

Страница 258: ...15 94 2 1050 66 8 738 66 2 738 89 8 1000 85 3 950 81 0 902 77 1 859 76 3 850 73 2 815 71 8 800 67 3 750 NOTES 412 S N 33001 through 33107 Pre TB 412 84 44 412 S N 33001 through 33107 Post TB 412 84 44...

Страница 259: ...g step If inspection does not reveal any discrepancies or obvious damage components may be retained in service 3 When torque has exceeded 100 for more than 3 seconds but has not exceeded 104 105 mast...

Страница 260: ...d reinstall oil lines Replace external oil filter element Remove and scrap oil cooler Install new oil cooler 2 If chip detector s and internal filter or full flow debris monitor as applicable appear n...

Страница 261: ...a Return the following components to an overhaul facility for overhaul evaluation NOTE Component removal record of dynamic components shall reflect overtorque as reason for removal 1 Transmission 2 M...

Страница 262: ......

Страница 263: ...ccurred Check helicopter and engine logs for any pertinent history AFTER ENGINE COMPRESSOR STALL OR SURGE Engine compressor stall or surge is characterized by a sharp rumble or a series of loud sharp...

Страница 264: ...for inspection requirements Chapter 63 Chapter 65 2 Power train a If compressor stall occurs below 85 N1 speed only step b and step c are required unless otherwise instructed in step c b Remove magne...

Страница 265: ...serviceable it may be reassembled and reinstalled for continued use If gear teeth are scored or scuffed or there is other damage that would render gearbox unserviceable gearbox shall be removed and an...

Страница 266: ...replacement Not applicable to 412 and 412SP 3 Disc pack coupling bolts Distortion or cracks in any bolt will require replacement Not applicable to 412 and 412SP 4 Tail rotor drive adapters Distortion...

Страница 267: ...in adjacent to tail rotor gearbox mounting Inspect all support structures in this area and repair as required Install new skin c Make close visual inspection of complete tailboom structure for distort...

Страница 268: ......

Страница 269: ...mage has been found in any area inspection shall be expanded in those areas until it extends beyond the zone of damage Any damage found anywhere on helicopter shall be recorded in detail and copies of...

Страница 270: ...412 CR O 1 Disassemble to extent required for cleaning and repacking coupling 2 Clean coupling 3 Visually inspect couplings for any evidence of arc burning or pitting Pay special attention to tips roo...

Страница 271: ...and hub If indications of burns or debonding are present send the blades to a Bell Helicopter Textron approved blade repair facility for evaluation State lightning strike as reason for removal Remove...

Страница 272: ...r from chip detector b Remove chip detector and reinstall connector c With electrical power applied to helicopter systems bridge chip detector gap with a clean screwdriver or other clean conductive ob...

Страница 273: ...rators and inverters for proper operation Visually inspect starter generators and inverters for burns or electrical arcing If damaged remove for internal inspection and bench test d Perform operationa...

Страница 274: ...upport for signs of lightning damage damaged finish and or burns If damage is evident remove supports and inspect mounting holes and mating surfaces for arcing damage Arcing damage shall be blended ou...

Страница 275: ..._______________ SIGNATURE _______________ _________________________ NOTE Accomplish after engine combining gearbox clutch nonengagement misengagement or in flight slippage A nonengaged engine is indic...

Страница 276: ...concave side Figure 5 7 NOTE Inspection mirrors and a suitable light are required The rotor must be turned slowly to permit inspection of all gear teeth BHT 412 CR O 3 Remove and replace any gear not...

Страница 277: ...NOTE If a tail rotor driveshaft has failed or yielded all tail rotor driveshafts hanger assemblies intermediate gearbox and tail rotor gearbox shall be replaced and tail rotor drive quill in transmiss...

Страница 278: ...in accordance with step 2 of step 2b If spiral bevel gear is damaged perform misengagement inspection given in step c of step 2 CONDITIONAL INSPECTIONS 5 43 AFTER ENGINE COMBINING GEARBOX CLUTCH NON E...

Страница 279: ...BHT 412 MM 2 5 00 00 26 FEB 2013 Rev 16 Page 229 Export Classification C ECCN EAR99 Figure 5 6 Fuselage Tailboom Attachment Inspection...

Страница 280: ...BHT 412 MM 2 5 00 00 Page 230 Rev 16 26 FEB 2013 Export Classification C ECCN EAR99 Figure 5 7 Spiral Bevel Gear Inspection Sheet 1 of 3...

Страница 281: ...BHT 412 MM 2 5 00 00 26 FEB 2013 Rev 16 Page 231 Export Classification C ECCN EAR99 Figure 5 7 Spiral Bevel Gear Inspection Sheet 2 of 3...

Страница 282: ...BHT 412 MM 2 5 00 00 Page 232 Rev 16 26 FEB 2013 Export Classification C ECCN EAR99 Figure 5 7 Spiral Bevel Gear Inspection Sheet 3 of 3...

Страница 283: ...ON COMMERCIAL HELICOPTERS CAUTION OVERHAUL SCHEDULE FOR SOME KIT COMPONENTS AND OR PARTS IS NOT COVERED IN THIS SCHEDULE REFER TO APPLICABLE SERVICE INSTRUCTIONS FOR KIT COMPONENTS SCHEDULE NOTE Refe...

Страница 284: ...10 100 Series Tail Rotor Hub Assembly 212 011 701 003 2500 hours Main Rotor Blades 412 015 200 300 Series POWER TRAIN Rotor Brake Quill 412 040 123 101 3000 hours Rotor Brake Quill 412 040 123 103 300...

Страница 285: ...412 040 366 111 113 5000 hours Mast Assembly 412 040 366 125 6000 hours Mast Assembly 412 040 366 129 6000 hours HYDRAULIC Flight Control Hydraulic Cylinders Cyclic and Collective 212 076 005 101 2500...

Страница 286: ...overhauled at time of transmission overhaul Incorporation of Increased Maximum Continuous Power Kit BHT 412 SI 38 P N 412 706 029 ALL reduces the time between overhaul TBO interval to 2500 hours Mast...

Страница 287: ...BHT 412 SI 74 412SP to 412HP Upgrade paragraph 5 32 Refer to Pratt Whitney Canada PT6T 3D Series Maintenance Manual for instructions on 2500 hour clutch inspection requirements The 10 100 hour inspec...

Страница 288: ......

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