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Textron Bell 412, Maintenance Manual

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Textron Bell 412 Maintenance Manual Download Page 247

BHT-412-MM-2

5-00-00

01 JUN 2018

Rev. 26

Page 199

Export Classification C, ECCN EAR99

(b)

If the main rotor mast assembly is not visibly

bent, twisted or distorted then the main rotor mast, main rotor
transmission assembly and rotor brake quill assembly (if
installed) shall have an overhaul evaluation performed. Make
an entry in the component records to show reason for removal
is a sudden stoppage.

(2)

If a sudden stoppage incident was confirmed but

the blade damage is confined to skin compression or wrinkling
behind the spar, perform the following inspection:

(a)

Remove main rotor blades, main rotor hub,

main rotor mast swashplate and support, hub and sleeve
assembly from helicopter. Remove main rotor transmission if
required.

(b)

Inspect mast assembly for distortion per

BHT-412-CR&O. Provided the mast assembly does not exceed
distortion limits, continue with step (c). If distortion exceeds
limits, the mast assembly shall be considered 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 case, mast

adapter, upper planetary assembly, upper sun gear, lower
planetary assembly, and lower sun gear. Visually inspect all
removed components as well as ring gear case for damage
resulting from sudden stoppage. If damage is found the main
rotor transmission and rotor brake quill (if installed) shall have
an overhaul evaluation performed. Make an entry in component
records to show reason for removal is a sudden stoppage.

(d)

If evaluation reveals no damage exceeding

limits in BHT-412-CR&O manual, reassemble transmission and
install main rotor mast, swashplate and support, hub and
sleeve, main rotor hub and main rotor blades. Annotate
component records as required.

2.

If the sudden stoppage was caused by a tail rotor strike do

the inspection that follows.

a.

Tail Rotor Hub and Blade assembly.

CONDITIONAL INSPECTIONS

5-38.

SUDDEN STOPPAGE — POWER ON OR OFF (CONT)

DATA REFERENCE

INSPECTION TASK DESCRIPTION

INITIAL

MECH      OTHER

Summary of Contents for Bell 412

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 6: ......

Page 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...

Page 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...

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

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 T...

Page 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...

Page 12: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 32: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 40: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 152: ......

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

Page 154: ......

Page 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...

Page 156: ......

Page 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...

Page 158: ......

Page 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...

Page 160: ......

Page 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...

Page 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...

Page 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...

Page 164: ......

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

Page 166: ......

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

Page 168: ......

Page 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...

Page 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...

Page 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...

Page 172: ......

Page 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...

Page 174: ......

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

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

Page 198: ......

Page 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...

Page 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...

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

Page 202: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 220: ......

Page 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...

Page 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...

Page 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...

Page 224: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 232: ......

Page 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...

Page 234: ......

Page 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...

Page 236: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 242: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 256: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 262: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 268: ......

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 288: ......

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