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Textron Bell 212 Скачать руководство пользователя страница 233

BHT-212-MM-1

5-00-00
Page 198

Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

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.

Sudden stoppage is defined as any rapid
deceleration of drive system whether caused by
seizure within helicopter transmission or by contact
of main or tail rotor blades with the ground, water,
snow, dense vegetation, trees, or other objects of
sufficient density to cause rapid deceleration. Main or
tail rotor blade damage, when caused by striking
some object sufficient to require blade replacement
(defined as removal for repair or scrap), is
considered sudden stoppage. When sudden
stoppage occurs, inspect helicopter and replace
components as follows:

1.

Perform a sudden stoppage inspection as follows:

NOTE

If sudden stoppage inspection is the result of a tail
rotor strike or main rotor blades striking the tail rotor
driveshaft, comply with

step g

through

step n

.

a.

Main rotor blades.

(1)

Visually inspect both main rotor blades for

evidence of damage. Check closely for wrinkled skin.

(2)

If any blade is damaged sufficiently to require

blade repair, return both blades to an authorized overhaul
facility. Make an entry in component record to show reason for
removal was sudden stoppage.

(3)

If no evidence of damage is found on either blade,

both blades may be retained in service.

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

DATA REFERENCE

INSPECTION TASK DESCRIPTION

INITIAL

MECH OTHER

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Содержание Bell 212

Страница 1: ...r Textron Inc and Airworthiness Directives AD issued by the applicable regulatory agencies shall be strictly followed Export Classification C ECCN 9E991 REISSUE 7 JUNE 1993 REVISION 16 15 NOVEMBER 2018 COPYRIGHT NOTICE COPYRIGHT 201 BELL HELICOPTER TEXTRON INC AND BELL HELICOPTER TEXTRON CANADA LTD ALL RIGHTS RESERVED MAINTENANCE MANUAL VOLUME 1 GENERAL INFORMATION ...

Страница 2: ...pter operation or maintenance is forbidden without prior written authorization from Bell Helicopter Textron Inc PN Rev 15 29 NOV 2013 DESTINATION CONTROL STATEMENT WARNING This document contains technical data whose export is restricted by the Arms Export Control Act Title 22 U S C Sec 2751 et seq or the Export Administration Act of 1979 as amended Title 50 U S C App 2401 et seq Violations of thes...

Страница 3: ...IS 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 PERFORMING ANY PROCEDURE CONTAINED IN THIS MANUAL YOU MUST INSPECT THE AFFECTED PARTS AND RECORDS FOR EVIDENCE OF ANY MANUFACTURE REPAIR REWORK OR USE OF A PROCESS NOT APPROVED BY BELL IF YOU IDENTIFY...

Страница 4: ...al Customer Service Engineering CSE network please access http www bellflight com support and service support Model 206 407 or 505 Phone 450 437 2862 or 800 243 6407 U S Canada Fax 450 433 0272 E mail productsupport bellflight com Model 222 230 427 429 or 430 Phone 450 437 2077 or 800 463 3036 U S Canada Fax 450 433 0272 E mail productsupport bellflight com Model 204 205 212 or 412 Phone 450 437 6...

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

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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 Reference No your initials and date If you choose to mail this form fold in thirds with address exposed tape and mail Export Classification C ECCN EAR99 ...

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

Страница 9: ...__________________________________________________ Future Publications to be mailed to this address Address ____________________________________________________________________ City _______________________________________________________________________ State Province _______________________________________________________________ Zip Postal Code ___________________________________________________...

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 TEXAS Export Classification C ECCN EAR99 ...

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

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Страница 24: ...er Occurs First Until 250 Hours 5 00 00 109 5 19 Between 5 and 10 Hours of Flight AFter Each Installation 5 00 00 115 5 20 Fin Spar Cap Inspection Every 8 Hours 5 00 00 117 5 21 Each 25 Hours for the next Four Inspections 5 00 00 119 5 22 Each 25 Hours of Flight Operation 5 00 00 121 5 23 Each 7 Days in a Corrosive Environment and Each 30 Days in a Noncorrosive Environment 5 00 00 127 5 24 50 Hour...

Страница 25: ... 00 00 165 5 43 Each 1000 Hours 12 Months of Main Rotor Blade Operation 5 00 00 169 5 44 Each 1200 Hours 24 Months of Component Operation 5 00 00 171 5 45 Each 1200 Hours of Main Rotor Hub Pin Operation Deleted 5 00 00 175 5 45A Every 12 months 2500 Landings High Forward Crosstube Deflection Check 5 00 00 176A 5 45B Every 12 months 5000 Landings High Forward Crosstube Fluorescent Penetrant Inspect...

Страница 26: ...ick Tube 104 5 4 Inspection of Main Rotor Hub Grip Tangs Barrel and Drag Brace Attachment Lugs 108 5 5 Spiral Bevel Gears Serial Numbers 111 5 6 Inspection of Spiral Bevel Gear 112 5 6A Tail Rotor Blade Detailed Inspection 126B 5 7 Inspection of Main Rotor Hub Grip 1200 Hours 24 Months 174 TABLES Table Page Number Title Number 5 1 Component Overhaul Schedule 231 15 NOV 2018 Rev 16 Page 3 4 ...

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Страница 28: ... helicopter may then be changed to the Part A inspection program beginning with a Daily Inspection The inspection intervals given in this chapter are the maximum permitted Do not exceed these intervals The owner operator is responsible for increasing the scope and the frequency of the inspections as necessary Make sure the helicopter is maintained safely during all unusual local changes such as en...

Страница 29: ...TION AND DEEMED UNAIRWORTHY SHALL BE PERMANENTLY MARKED AS SCRAP OR PHYSICALLY DESTROYED TO THE EXTENT THAT THERE IS NO CHANCE OF REPAIR OR INSTALLATION ON ANY HELICOPTER OR COMPONENT 5 Make sure all limited life parts that have completed their published operating limits are replaced 6 Make sure all of the components that have completed their published overhaul periods are overhauled 7 Make sure a...

Страница 30: ...thiness Limitations Schedule Chapter 4 3 Lubrication and servicing requirements are in addition to those stated in this chapter Chapter 12 4 For corrosion control refer to the Corrosion Control Guide CSSD PSE 87 001 and the BHT ALL SPM 5 For the PT6T 3 3B engines refer to the Pratt Whitney Canada Maintenance Manual for the scheduled inspection special inspection conditional inspection and componen...

Страница 31: ...roved product improvement or a change to a maintenance interval The engineering aspects of this change are approved The program is closely monitored by Bell Helicopter Textron in an operational environment with selected operators Special Programs These are approved programs that may be initiated under certain special conditions to meet specific requirements These programs will be clearly defined t...

Страница 32: ...10 2010 10 of 12 months 1 2 months maximum allowed is 30 days July 8 2010 within 30 day tolerance July 31 2011 July 31 2011 10 of 12 months 1 2 months maximum allowed is 30 days June 15 2011 completed early June 30 2012 June 30 2012 10 of 12 months 1 2 months maximum allowed is 30 days June 30 2012 tolerance not applied June 30 2013 NOTE The last day of the month applies for the next inspection pa...

Страница 33: ...E AT 6000 Hours December 31 2010 10 of 3000 hours 300 hours maximum allowed is 100 hours or 10 of 60 months 6 months maximum allowed is 30 days 6000 Hours January 15 2011 within 30 day calendar tolerance 9000 Hours January 31 2016 9000 Hours January 31 2016 10 of 3000 hours 300 hours maximum allowed is 100 hours or 10 of 60 months 6 months maximum allowed is 30 days 9100 Hours January 2 2016 100 h...

Страница 34: ... 7 SCHEDULED INSPECTIONS Part A Inspect helicopter daily each 100 hours 12 calendar months each 1000 hours each 3000 hours 5 years Part B Inspect helicopter each 25 hours 30 days each 300 hours each 600 hours 12 calendar months each 3000 hours 5 years 26 JUN 2013 Rev 14 Page 11 12 ...

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Страница 36: ...tion 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 referenced Maintenance Manual or BHT 212 CR O manual chapter specified 2 Refer to the Pratt Whitney Canada PT6T 3 3B Maintenance Manual for engine inspection requirements PRELIMINARY REQUIREMENTS Corrosion Control Guide C...

Страница 37: ...ucture for damage and corrosion 2 Visually inspect overhead ventilating system components for condition and security 3 Visually inspect heat vent air ducts for condition and security 4 Visually inspect ventilation defog components for condition and security Chapter 25 CREW PASSENGER SEATS 1 Visually inspect crew seats for condition security and operation 2 Visually inspect crew seats restraints fo...

Страница 38: ...and security c Hydraulic system 1 and 2 pumps for leaks damage and security d Hydraulic system 1 and 2 valve and filter modules for leaks damage and security e Hydraulic system 1 and 2 lines hoses and fittings for leaks damage chafing kinking and security f Hydraulic system 1 and 2 reservoirs for proper fluid levels damage corrosion and security g Tail rotor hydraulic actuator and hoses for leakag...

Страница 39: ...ity in area of attachment f Emergency float reservoir pressure indicator for proper charge indication if installed g Floats for proper stowage and condition if installed 2 Visually inspect tail skid for deformation and security of attachment Chapter 52 DOORS WINDOWS AND EMERGENCY EXIT 1 Visually inspect nose door for obvious damage security of attachment proper latching and seal for condition 2 Vi...

Страница 40: ... cracks and proper operation of latches 4 Inspect tailboom fuselage attachment points for security 5 Pitot tube s and static ports for obstruction and damage 6 Fuselage interior for evidence of water entrapment a Nose compartment b Pilot and passenger cabin c Electrical compartment d Heater compartment e Baggage compartment Chapter 53 TAILBOOM 1 Inspect tailboom exterior structure for general cond...

Страница 41: ... evidence of cracks at pillow block bushing bores Proper sealing of pillow blocks yoke and attaching through bolts washers nuts and bushings 4 Inspect blade retention bolts for condition and security Chapter 62 MAIN ROTOR CONTROLS Detailed Visual Inspection 1 Swashplate and support assembly and collective lever for condition and security 2 Scissors and sleeve assembly for security and condition 3 ...

Страница 42: ...gradation step 3 If one or more of the red bordered TEMP PLATE dots change from white off white to black an overheat condition is present and may require replacement of both outer and inner couplings 3 Visually inspect overheat TEMP PLATES for condition and security TEMP PLATES must not show evidence of overtemperature indication deterioration debonding or excessive discoloration of the epoxy over...

Страница 43: ... ANY DISCOLORATION SHALL BE DETERMINED AND CORRECTED PRIOR TO NEXT FLIGHT 7 Transmission tail rotor output quill coupling and surrounding area 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 red bordered TEMP PLATE dots from white off white to black indicates an overheat condition and may req...

Страница 44: ... obstruction 2 Oil cooler hoses and tubes for leaking damage chafing and fraying 3 Oil cooler blowers for damage and obstruction Chapter 64 TAIL ROTOR HUB AND BLADE ASSEMBLY Detailed Visual Inspection WARNING NO CRACKS ARE PERMITTED ON ANY SURFACE OF THE TAIL ROTOR BLADES 1 Tail rotor blades for condition of bond lines cracks corrosion leading edge erosion damage security and cleanliness Clean bla...

Страница 45: ...left 6 Pitch change links for binding with tail rotor blade moved to both full flapping positions Binding is not acceptable Chapter 65 TAIL ROTOR DRIVESHAFT 1 Hanger assemblies bearings and surrounding areas for evidence of grease leakage condition damage security corrosion and overheating Discoloration of bearing color change to blue to blue black in color or multi color appearance of hanger that...

Страница 46: ...MP PLATE dots from white off white to black indicates an overheat condition and may require replacement 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 discoloration of the epoxy overcoating Chapter 65 INTERMEDIATE GEARBOX Detailed Visual Inspection 1 Ge...

Страница 47: ...rheat condition and may require replacement of both outer and inner couplings step 3 3 Overheat TEMP PLATES for condition and security TEMP PLATES must not show evidence of over temperature indication deterioration debonding or excessive discoloration of the epoxy overcoating 4 Gearbox for proper oil level and oil for evidence of contamination 5 Gearbox assembly for security condition corrosion da...

Страница 48: ... and inner couplings 3 Overheat TEMP PLATES for condition and security TEMP 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 contamination Chapter 67 ELEVATORS Detailed Visual Inspection 1 Elevators for damage and security Chapter 71 LEFT POWER SECTION Detai...

Страница 49: ...apter 71 REDUCTION GEARBOX Detailed Visual Inspection 1 Hoses and lines for security leaks and chafing 2 Oil filter impending bypass indicator button not extended 3 Proper oil level Chapter 71 ENGINE AND REDUCTION GEARBOX MOUNTS Detailed Visual Inspection 1 Mounts for loose bearings and security ENGINE FIREWALLS Detailed Visual Inspection 1 Firewalls for cracks distortion missing rivets broken spo...

Страница 50: ...or cleanliness 2 All instruments placards decals and markings for appearance and legibility 3 Check magnetic compass for condition and security 4 All compass cards for validity Chapter 96 ELECTRICAL SYSTEMS General Visual Inspection 1 Nose compartment electrical equipment for condition and security 2 Pedestal mounted avionics electrical equipment for condition cleanliness and security 3 Overhead c...

Страница 51: ... and security Chapter 96 BATTERY SYSTEM General Visual Inspection 1 Battery and external connections for condition and security 2 Battery vent and drain tubes for obstruction and security Chapter 97 ANTENNAS 1 Visually inspect all antennas located on fuselage and tailboom for condition and security Chapter 97 AVIONICS EQUIPMENT 1 Visually inspect all avionics located in fuselage and tailboom for c...

Страница 52: ... 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 accordance with the referenced maintenance manual chapter specified or BHT 212 CR O manual 2 Refer to Pratt Whitney Canada PT6T 3 3B Maintenance Manual for engine inspection requirements 3 Record all work accomplished d...

Страница 53: ...apter 21 HEAT VENT AIR DUCTS 1 Visually inspect all heating ventilation cooling ducts and controls for cracks security and proper operation Every sixth 100 hour inspection 600 hours or 12 months 2 Bleed air heating and ventilation defog system components a Perform functional check of bleed air heating system and components b Perform functional check of defog blower Chapter 25 MISCELLANEOUS FURNISH...

Страница 54: ...2 Remove four access doors located just forward of the aft crosstube from the underside of the fuselage Inspect fuel lines for evidence of leakage damage and security Chapter 29 HYDRAULIC SYSTEMS 1 Inspect all lines and hoses for security and general condition Every sixth 100 hour 600 hours inspection or 12 months NOTE Hydraulic filter elements 205 076 034 003 are non cleanable It is recommended t...

Страница 55: ...e indicator for proper charge indication 2 If installed floats for proper stowage and condition 3 Landing gear crosstube assemblies skid tubes and skid shoes for condition and security of attachment Inspect crosstube retention cap rubber bumper pads for condition and security of attachment 4 Tail skid for deformation and security of attachment 5 Fuselage supports for wear damage and security of at...

Страница 56: ...lowing inspection step 3 and step 4 is for helicopters equipped with escape panels which may be identified by a rotating handle installed below the passenger door windows The handle is labeled EMERGENCY RELEASE PULL COVER TURN LEFT AND PUSH 3 Inspect passenger door emergency egress panel pins and mechanisms for wear corrosion operation and security 4 Perform operational check of passenger door esc...

Страница 57: ...ches 101 6 mm below upper tailboom skin as follows Remove aft tailboom access door Face aft and use bright light and small mirror to inspect area for cracks especially near rivet holes NOTE If necessary clean area with cloth dampened with MEK C 309 or equivalent Ventilate area to prevent breathing fumes Every third 100 hour inspection 300 hours or every 12 months 1 Inspect tailboom joints splices ...

Страница 58: ... cap angle Figure 5 1 3 Move pylon fore and aft Using mast as lever check friction dampers for freedom of movement and smooth operation 4 Inspect transmission mounts mounting brackets and structure for cracked or broken parts 5 Inspect lift link and fitting for cracks and security 6 Cabin interior and exterior for corrosion and damage 7 All compartments for evidence of water entrapment and corrosi...

Страница 59: ...spection 600 hours or 12 months 1 Fuselage cabin structure a Fuselage structure for corrosion and damage to finish and sealant Pay particular attention to edges of joints and seams and around fastener heads b Engine compartment floor and service deck at FS 155 06 to 241 22 for damage delamination and corrosion NOTE To adequately inspect the following it will be necessary to remove the auxiliary fu...

Страница 60: ...00 at FS 129 00 Figure 5 2 Detail A and Detail B 3 Apply clear lacquer over cleaned area Chapter 62 MAIN ROTOR BLADE INSPECTION SYSTEM BIS Inspect BHT 212 CR O and Chapter 96 1 Test detector unit 2 Perform continuity check on blade conductor circuits 3 Remove BIS battery 4 Perform battery condition check on replacement battery Install replacement battery Chapter 62 MAIN ROTOR BLADES 1 Wash main ro...

Страница 61: ...presence of black oxide powder will require investigation to determine the cause b Inspect gimble ring bearings liners and attaching hardware for excessive looseness and wear Gimble ring bearing and attaching bolt axial or radial looseness shall not exceed 0 005 inch 0 127 mm and no binding is allowed 2 Disconnect flight control tubes from swashplate and collective lever assembly Inspect six trunn...

Страница 62: ... leakage 4 Check all transmission chip detectors for debris and then clean 5 Test all transmission chip detectors electrical circuits 6 Every third 100 hour inspection 300 hours check internal oil filter or full flow oil monitor for debris and then clean 7 Every third 100 hour inspection 300 hours torque check top case to ring gear case nuts ring gear case to main case nuts and main case to suppor...

Страница 63: ...R BLADES 1 Inspect the tail rotor counterweight bellcrank P N 212 011 705 001 retention nuts for cracks corrosion and security Reapply corrosion preventive compound C 101 if nuts are not completely covered Every third 100 hour inspection 300 hours or every 12 months Chapter 18 1 Dynamically balance tail rotor 2 Torque check nuts on tail rotor blade retention bolts 3 Torque check tail rotor retaini...

Страница 64: ...t hole lugs Chapter 65 INTERMEDIATE GEARBOX 1 Inspect chip detector for debris If metallic particles are found determine and correct cause 2 Clean chip detector 3 Test chip detector electrical circuit Chapter 67 ELEVATOR Detailed Visual Inspection 1 Elevators for security cracks damage loose or missing rivets and corrosion 2 Check elevator attachment lugs at each end of elevator horn for cracks an...

Страница 65: ... 4 Trailing edge tabs and tip caps for condition and security Every sixth 100 hour inspection 600 hours or 12 months 1 Remove left and right elevators 2 Clean elevator spars and inspect for corrosion 3 Clean internal bore of elevator horn and inspect for corrosion 4 With elevator control removed attach a spring scale to hole in arm of horn where control tube is normally installed Pull scale at rig...

Страница 66: ... range of travel 2 Cyclic flight controls a Flight control systems bellcrank and control 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 applicable to AFCS equipped helicopters d Check cyclic flight controls for smooth movement throughout full range of travel 3 Anti torque flight co...

Страница 67: ...y corrosion preventive compound C 104 as required 8 Actuator linkage for wear and security 9 Clean exposed area of actuator piston with hydraulic fluid C 002 or hydraulic fluid C 072 and a clean lint free cloth 10 Check cyclic and collective hydraulic cylinders piston rods for evidence of excessive wear and scoring Wear of the piston rods indicates cylinder assembly is incorrectly aligned to lower...

Страница 68: ...spect the left hand and right hand engine air inlet cowlings for gaps between the lower surface of the cowling firewall and the mating horizontal engine firewall Chapter 71 LEFT POWER SECTION NOTE Refer to Pratt Whitney Canada PT6T 3 3B Maintenance Manual for engine inspection requirements Every third 100 hour inspection 300 hours or 12 months Detailed Visual Inspection 1 Ignition leads for corros...

Страница 69: ...n chip detectors Functional Check 1 Test chip detectors electrical circuits Chapter 76 ENGINE FUEL AND POWER CONTROLS Every third 100 hour inspection 300 hours or 12 months Operational Check 1 Check controls for smooth movement through full travel ranges Chapter 71 STARTER GENERATOR Every third 100 hour inspection 300 hours or 12 months Detailed Visual Inspection 1 Left power section starter gener...

Страница 70: ...uel and power controls a Engine control linkages for looseness lost motion chafing damage and security of attachment b Bellcranks mounts and jackshafts for looseness damage and security of attachment Every sixth 100 hour inspection 600 hours or 12 months 1 Perform maximum NG topping check Chapter 71 COMBINING REDUCTION GEARBOX NOTE Refer to Pratt Whitney Canada PT6T 3 3B Maintenance Manual for eng...

Страница 71: ...RICAL SYSTEM 1 Check inverters for security of mounting and connections 2 Check generator control units for damage and security of mounting and terminals 3 All exposed wire bundles bundle supports and connectors for damage corrosion and security Pay particular attention to engine deck connectors and harnesses 4 Inspect relays and main bus area for security of mounting and connections 5 Inspect bus...

Страница 72: ...s recommendation 2 Inspect battery compartment for general condition 3 Check battery mount for security and corrosion Chapter 96 POWER DIODES Every third 100 hour inspection 300 hours or 12 months 1 Perform functional check of power diodes SCHEDULED INSPECTIONS 5 9 100 HOURS 12 CALENDAR MONTHS PART A CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 73: ...BHT 212 MM 1 5 00 00 Page 50 Rev 14 26 JUN 2013 Export Classification C ECCN EAR99 Figure 5 1 Fuselage Tailboom Attachment Inspection ...

Страница 74: ...BHT 212 MM 1 5 00 00 Export Classification C ECCN EAR99 Figure 5 2 Inspection of Beam Caps 26 JUN 2013 Rev 14 Page 51 52 ...

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Страница 76: ..._______________________ NOTE For helicopters on the Part A inspection program accomplish the following checks each 1000 hours of flight operation GENERAL Instruction 1 Each listed inspection item or maintenance function is to be performed in accordance with this Maintenance Manual 2 All work accomplished during the inspection shall be recorded in the helicopter maintenance record 3 Accomplish comp...

Страница 77: ... trunnion and each mixing lever control tube from scissors 3 Check swashplate duplex bearing and collective sleeve hub bearing set for roughness and ease of rotation 4 Purge lubricate bearings 5 Reconnect drive links and tubes SCHEDULED INSPECTIONS 5 10 1000 HOURS PART A CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 78: ...__ NOTE For helicopters on the Part A inspection program accomplish each 3000 hours of flight operation or 60 calendar months whichever occurs first GENERAL Instruction 1 Each listed inspection item or maintenance function is to be performed in accordance with the Maintenance Manual chapter specified or BHT 212 CR O manual PRELIMINARY REQUIREMENTS 1 All work accomplished during inspection shall be...

Страница 79: ...clic and anti torque control system bellcranks levers and support brackets for corrosion cracks and indication of wear at attaching points 5 Crew seat support beams at BL 14 0 and 30 0 and FS 23 0 and 74 30 for cracks and corrosion 6 Forward crosstube attach points and support structure at FS 63 33 and 74 30 for damage corrosion and cracks Aft crosstube attach points and support structure at FS 15...

Страница 80: ...nt interior for condition joints for corrosion skin for damage and cracks 13 Oil cooler compartment FS 166 0 to 243 937 Doors for condition and security Main beam panels and bulkheads for condition and corrosion 14 Firewalls FS 155 06 to 241 22 for seal wear and damage cracks and attachment 15 Cabin roof FS 35 0 to 166 0 above WL 68 0 BL 50 left and right Skin and joints for corrosion and damage 1...

Страница 81: ...tment for damage delamination and corrosion Chapter 28 FUEL SYSTEM 1 Inspect fuel cells for condition and serviceability Verify self sealing gum of the lower cells has not been activated Repairs to be accomplished at an authorized facility Chapter 67 BHT212 CR O BHT 212 SI 4 BHT 212 SI 89 TB 212 87 98 FLIGHT CONTROLS 1 Disassemble pilot and copilot collective sticks if installed to the extent nece...

Страница 82: ...EAR99 5 Check throttle controls for proper operation 6 Check collective controls for proper operation SCHEDULED INSPECTIONS 5 11 3000 HOURS 5 YEARS PART A CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER 26 JUN 2013 Rev 14 Page 59 60 ...

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Страница 84: ...gram 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 the referenced Maintenance Manual chapter specified or BHT 212 CR O manual 2 Refer to Pratt Whitney Canada PT6T 3 3B Maintenance Manual for engine inspection requirements PRELIMINARY REQUIREMENTS...

Страница 85: ...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 Avionics and electrical compartment for water entrapment Chapter 96 4 Battery installation a Battery and external connections for security corrosion and condition b Battery vent and drain tubes are unobstructed c Every fourth...

Страница 86: ...raulic fluid leakage Chapter 28 3 Visually inspect fuel samples for contamination Chapter 32 4 Landing gear system a Forward crosstube assembly and retention caps for condition and security of attachment b Aft crosstube assembly and retention caps for condition and security of attachment c Skid tubes and skid shoes for condition and security of attachment Replace skid shoes that are worn into shoe...

Страница 87: ...backs for cleanliness excessive deterioration and tears c Crew seat restraint assemblies for condition security and proper operation Chapter 25 9 Passenger seats a Seats for condition and security b Cushions and backs for cleanliness excessive deterioration and tears c Passenger seat restraint assemblies for condition security and proper operation Chapter 95 10 Instruments a Instrument panel for c...

Страница 88: ...n lights for condition and security g Every fourth 25 hour 30 day inspection operationally check cabin heater system bleed air shutoff and line check valve Chapter 26 12 Two portable fire extinguishers for condition mounting and valid inspection certificate Chapter 21 13 Cabin heating and ventilation system a Ventilating system components for condition and security b Heat vent air ducts for condit...

Страница 89: ...area 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 red bordered TEMP PLATE dots from white off white to black indicates an overheat condition and may require replacement of both outer and inner couplings step h h Overheat TEMP PLATES for condition and security TEMP PLATES must not show evid...

Страница 90: ...ent and helicopters modified in accordance with TB 212 76 12 1 Clean area around fuel vent line hole with MEK C 309 and remove finish from beam cap 2 Inspect each beam cap for hairline cracks using a bright light Inspect inboard side of left and right main beams around fuel vent line that goes through cap extrusion at FS 131 00 WL 21 50 and BL 14 00 Pay particular attention to first high shear riv...

Страница 91: ...otor hydraulic actuator and hoses for leakage corrosion and security Chapter 67 6 Tail rotor control tubes for condition corrosion and security Chapter 63 7 Transmission oil cooling system a Oil coolers for leakage damage and obstruction b Oil cooler hoses and tubes for leakage damage chafing and fraying c Oil cooler blowers for damage corrosion and obstruction Chapter 79 8 Engine oil system a Oil...

Страница 92: ...nd tubes for chafing leaking and security d Electrical wiring for fraying chafing and security Chapter 71 12 No 2 right engine power section a Exhaust ejector and duct for damage and security b Gas generator case for cracks buckled areas and hot spots c Oil and fuel hoses and tubes for chafing leaking and security d Electrical wiring for fraying chafing and security Chapter 71 13 Engine firewalls ...

Страница 93: ...ion and cleanliness Chapter 52 2 Baggage compartment door for damage proper operation and security Chapter 52 3 Driveshaft and intermediate gearbox covers for damage and security Chapter 67 4 Elevators for damage and security Chapter 97 5 Tailboom mounted avionics equipment for condition and security Chapter 53 6 Every fourth 25 hour 30 day inspection ASB 212 00 110 a Inspect vertical fin caps for...

Страница 94: ...SHALL BE DETERMINED AND CORRECTED PRIOR TO NEXT FLIGHT a Hanger assemblies bearings and surrounding areas for evidence of grease leakage condition damage security corrosion and overheating Discoloration of bearing color change to blue or blue black or multi color appearance of hanger that darkens adjacent to bearing is evidence of overheating Brown color of bearing shield is normal and is not evid...

Страница 95: ...idence of over temperature indication deterioration debonding or excessive discoloration of the epoxy overcoating Chapter 65 8 Intermediate gearbox a Gearbox assembly for security condition corrosion damage and oil leaking WARNING THE CAUSE OF ANY DISCOLORATION SHALL BE DETERMINED AND CORRECTED PRIOR TO NEXT FLIGHT b Input and output quill flexible couplings and surrounding area for grease leakage...

Страница 96: ...b Input quill flexible coupling and surrounding area 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 red bordered TEMP PLATE dots from white off white to black indicates an overheat condition and may require replacement of both outer and inner couplings step c c Overheat TEMP PLATES for condi...

Страница 97: ...oseness and freedom of movement through full range of travel with anti torque pedals positioned full right and then full left d Tail rotor pitch change links crosshead pitch horns counterweight arms and links for security corrosion and condition e Pitch link bearing and counterweight link bearing looseness shall not exceed 0 015 inch 0 381 mm axial Check freedom of movement through full range of t...

Страница 98: ...2 011 705 001 retention nuts for cracks corrosion and security Reapply corrosion preventive compound C 101 if nuts are not completely covered Chapter 32 12 Tail skid for deformation and security of attachment CABIN ROOF Chapter 52 and Chapter 53 1 Cabin structure and cowlings fairings for condition Chapter 63 2 Transmission and transmission oil lines for condition corrosion and leaks Chapter 63 an...

Страница 99: ...ur 30 day inspection wash main rotor blades with mild soap and water Rinse and dry thoroughly Chapter 62 6 Main rotor hub Detailed Visual Inspection a Main rotor hub assembly grips drag braces trunnion pillow blocks static stops and mast nut for condition and security b Hub assembly for proper oil level or grease lubrication c Main rotor yoke for evidence of cracks at pillow block bushing bores Pr...

Страница 100: ...ngs 180 and purge lubricate c Scissors and sleeve assembly for security and condition Collective lever for condition and evidence of corrosion d Every fourth 25 hour 30 day inspection replace bearings MS20201KP8A or MS27641 8 in scissors levers 204 011 406 e Pitch links damper tubes and connecting links for condition and security Bearings for looseness f Stabilizer bar dampers for condition securi...

Страница 101: ...uplings boots seals and surrounding area for grease leakage damage corrosion and evidence of overheat as indicated by TEMP PLATES or coupling discoloration A change in color of any yellow bordered TEMP PLATE 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 ...

Страница 102: ...NOTE For helicopters on the Part B inspection program accomplish the following checks each 300 hours of flight operation GENERAL Each listed inspection item or maintenance function is to be performed in accordance with the chapter specified PRELIMINARY REQUIREMENTS 1 All work accomplished during inspection shall be recorded in helicopter maintenance records 2 Remove all panels fairings and cowling...

Страница 103: ... c Evidence of excessive fluid leakage d Structure around landing gear for condition e Forward crosstube support structure for working fasteners cracks corrosion and excessive wear f Aft crosstube support structure for working fasteners cracks corrosion and excessive wear Chapter 52 3 Doors and windows a Crew and passenger doors structure for corrosion damage distortion and positive locking mechan...

Страница 104: ...rs if applicable for damage f Nose electrical and equipment compartment access doors for corrosion damage distortion and positive locking mechanisms g Inspect heated windshield if installed for condition and proper operation Chapter 67 4 Collective flight control actuator a Universal bearings for looseness b Input lever bearings and bolts for wear and looseness c Fasteners attaching cylinder lower...

Страница 105: ...vity for corrosion Cavity drain hole for obstruction Reapply corrosion preventive compound C 104 as required Dust boot for condition Chapter 67 5 Collective control tubes a Control tubes between collective jackshaft and collective control actuator pilot valve input lever for corrosion wear and damage b Control tube bellcrank supports and attaching hardware for corrosion wear and damage Chapter 67 ...

Страница 106: ...cylinder housing mounting bracket cavity for corrosion Cavity drain hole for obstruction Reapply corrosion preventive compound C 104 as required Dust boot for condition Chapter 67 7 Cyclic control tubes a Control tubes between cyclic jackshaft and cyclic control actuator pilot valve input lever for corrosion wear and damage b Control tube bellcranks mixing levers supports and attaching hardware fo...

Страница 107: ...able seals or refer to Chapter 71 for seal adjustment ASB 212 10 137 1 Inspect the left hand and right hand engine air inlet cowlings for gaps between the lower surface of the cowling firewall and the mating horizontal engine firewall LEFT POWER SECTION Chapter 71 NOTE Refer to Pratt Whitney Canada PT6T 3 3B Maintenance Manual for engine inspection requirements 1 Chip detectors for debris 2 Clean ...

Страница 108: ...itney Canada PT6T 3 3B Maintenance Manual for engine inspection requirements 1 Chip detectors for debris 2 Clean chip detector 3 Test chip detector electrical circuits Chapter 71 STARTER GENERATOR 1 Left power section starter generator brushes for allowable wear 2 Right power section starter generator brushes for allowable wear 3 Left power section starter generator cooling ducts for obstruction k...

Страница 109: ...tube saddle bolts 3 Torque check forward and aft crosstube support fittings U bolts 80 to 100 inch pounds 9 0 to 11 3 Nm 4 Torque check ground handling wheel attachment eyebolts on skid tubes 40 to 58 foot pounds 54 to 79 Nm Eyebolts that rotate prior to reaching 40 foot pounds 54 Nm shall be removed and inspected for evidence of bending No bending is permitted Chapter 26 FIRE DETECTION SYSTEM Gen...

Страница 110: ...g button with sealant C 308 h Ensure all drain holes are open i Vertical fin spar caps forward side and web from upper tailboom skin to approximately 4 inches 101 6 mm below upper tailboom skin as follows remove aft tailboom access door Face aft and use bright light and small mirror to inspect area for cracks especially near rivet holes BHT ALL SPM NOTE If necessary clean area with cloth dampened ...

Страница 111: ...ce near attachment bolt for radial measurement Applying light force to move elevator in required direction check that radial movement does not exceed 0 010 inch 0 254 mm and that axial movement is within 0 005 to 0 030 inch 0 127 to 0 762 mm Adjust shims as required d Elevator rigging for proper setting and travel Chapter 52 4 Baggage compartment door for corrosion damage distortion and positive l...

Страница 112: ...or gearbox a Chip detector for debris b Clean chip detector c Functionally test chip detector electrical circuit Chapter 12 d Service gearbox as required Chapter 64 10 Tail rotor hub and blade assembly a Torque check nuts on tail rotor blade retention bolts b Torque check tail rotor hub retaining nut Chapter 18 c Dynamically balance tail rotor Chapter 62 MAIN ROTOR BLADE INSPECTION SYSTEM BIS IF I...

Страница 113: ...stall replacement battery Chapter 52 and Chapter 53 CABIN ROOF 1 Cabin roof structure a Cabin roof structure cowlings and fairings for damage delamination and general condition b Cabin roof and cowling fairing mounted antennas for condition and security SCHEDULED INSPECTIONS 5 13 300 HOURS PART B CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 114: ...________________ NOTE For helicopters on the Part B inspection program accomplish the following checks each 600 hours flight time or 12 calendar months whichever occurs first GENERAL Each listed inspection item or maintenance function is to be performed in accordance with the 212 Maintenance Manual chapter specified PRELIMINARY REQUIREMENTS 1 All work accomplished during inspection shall be record...

Страница 115: ...s Chapter 52 3 Perform operational check of crew doors emergency release mechanisms Chapter 21 and Chapter 96 4 Bleed air heating and ventilation defog system components a Perform functional check of bleed air heating system and components b Perform functional check of defog blower Chapter 95 5 Instruments required at 12 months calendar time only a Calibrate pilot and copilot compass systems and s...

Страница 116: ... flight controls a Flight control systems bellcrank and control tubes for damage chafing corrosion and security of attachment b Functionally check cyclic stick friction adjuster for proper friction and operation c Functionally check cyclic flight controls for smooth movement throughout their full travel ranges Chapter 67 9 Anti torque flight controls a Flight control systems bellcrank and control ...

Страница 117: ...tem bellcranks mounts and control tubes for damage chafing corrosion and security of attachment b Functionally check collective lever throttle friction adjusters for proper friction and operation c Functionally check engine controls for smooth movement throughout their full travel ranges 13 Inspect all exposed fuel lines and attachments for leakage damage and security Chapter 29 14 Hydraulic syste...

Страница 118: ...ess 0 150 inch 3 81 mm Chapter 53 15 Fuselage cabin structure a Fuselage structure for corrosion and damage to finish and sealant Pay particular attention to edges of joints and seams and around fastener heads b Ensure all drain holes are open c Engine compartment floor and service deck FS 155 06 to 241 22 for damage delamination and corrosion d Fuselage bonded panels for damage and delamination N...

Страница 119: ...er firing cartridges in accordance with specified service life Chapter 28 19 Remove four access doors located just forward of the aft crosstube from the underside of the fuselage Inspect fuel lines for evidence of leakage damage and security NOTE The following step is to be performed every 12 months 20 Inspect all fuel system oil system and hydraulic system filler caps for proper functioning and s...

Страница 120: ...horn and inspect for corrosion d With elevator control removed attach a spring scale to hole in arm of 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 left and right elevators SCHEDULED INSPECTIONS 5 14 600 HOURS 12 MONTHS PART B CONT DATA REFERENCE ...

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Страница 122: ...helicopters on the Part B inspection program accomplish the following checks each 3000 hours flight time or 60 calendar months whichever occurs first GENERAL Each listed inspection item or maintenance function is to be performed in accordance with the maintenance manual chapter specified PRELIMINARY REQUIREMENTS 1 All work accomplished during inspection shall be recorded in helicopter maintenance ...

Страница 123: ...dication of wear at attaching points 5 Crew seat support beams at BL 14 0 and 30 0 and FS 23 0 and 74 30 for cracks and corrosion 6 Forward crosstube attach points and support structure at FS 63 33 and 74 30 for damage corrosion and cracks Aft crosstube attach points and support structure at FS 155 06 and 166 00 for damage corrosion and cracks 7 Crew and passenger cabin floor FS 23 0 to 155 06 for...

Страница 124: ...37 doors for condition and security Main beam panels and bulkheads for condition and corrosion 14 Firewalls FS 155 06 to 241 22 for seal wear damage cracks and security of attachment 15 Cabin roof FS 35 0 to 166 0 above WL 68 0 BL 50 0 left and right for damaged skin and joints for corrosion 16 Bulkhead FS 241 22 for corrosion and cracks Tailboom attach bolt holes for damage and corrosion TAILBOOM...

Страница 125: ...M 1 Inspect fuel cells for condition and serviceability Verify self sealing gum of the lower cell has not been activated Repairs to be accomplished at an authorized facility Chapter 67 BHT 212 CR O BHT 212 SI 4 BHT 212 SI 89 TB 212 87 98 FLIGHT CONTROLS 1 Disassemble pilot and copilot collective sticks if installed to the extent necessary to remove throttle twist grips 2 Referring to Figure 5 3 vi...

Страница 126: ...Export Classification C ECCN EAR99 5 Check throttle controls for proper operation 6 Check collective controls for proper operation SCHEDULED INSPECTIONS 5 15 3000 HOURS 5 YEARS PART B CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 127: ...BHT 212 MM 1 5 00 00 Page 104 Rev 14 26 JUN 2013 Export Classification C ECCN EAR99 Figure 5 3 Collective Stick Tube 212_MM_05_0009 ...

Страница 128: ...100 hours after installation of tailboom 16 Each 150 hours of starter generator operation 17 Fin spar cap inspection every 300 hours 18 Each 300 hours 12 months of transmission operation 19 Each 300 hours 3 months of driveshaft operation 20 Main rotor grip ultrasonic inspection 21 Each 500 hours or 6 months of blade service 22 Each 600 hours of transmission operation 23 Each 600 hours 6 months of ...

Страница 129: ... the tare torque listed in the BHT ALL SPM Chapter 2 Looseness may occur until components seat themselves and fasteners are tightened This is not cause for disassembly however the fastener will have to be torque checked again at the same scheduled interval set for the first torque check until the assembly is completely seated For additional information refer to BHT ALL SPM If any confusion exists ...

Страница 130: ...________ Chapter 62 MAIN ROTOR HUB GRIP 204 011 121 009 Detailed Visual Inspection 1 For 204 011 121 009 main rotor grip inspect grip barrels both leading and trailing sides for evidence of hairline cracks Figure 5 4 NOTE The following inspection is required for main rotor grips 204 011 121 009 with 15000 hours or more Time In Service TIS ASB 212 14 150 2 Visually inspect the outboard face and edg...

Страница 131: ...BHT 212 MM 1 5 00 00 Page 108 Rev 16 15 NOV 2018 Export Classification C ECCN EAR99 Figure 5 4 Inspection of Main Rotor Hub Grip Tangs Barrel and Drag Brace Attachment Lugs ...

Страница 132: ...______________________ NOTE Accomplish daily or each 10 hours flight operation whichever occurs first until 250 hours on transmission with affected gears with 50 hours or more Chapter 63 and ASB 212 89 54 SPIRAL BEVEL GEAR 204 040 701 103 Inspect NOTE This inspection is only applicable to transmissions helicopters with the spiral bevel gears shown in Figure 5 5 installed 1 Remove and inspect the t...

Страница 133: ...ts set forth in step b Notify Product Support Engineering of serial number and total time of any gear replaced d Install quill pad cover or rotor brake quill 3 Spare uninstalled affected spiral bevel gears a Return spare affected serial numbered spiral bevel gears to Bell Helicopter Textron for inspection and reidentification Refer to Information Letter IL GEN 04 98 for shipping instructions SPECI...

Страница 134: ...BHT 212 MM 1 5 00 00 26 JUN 2013 Rev 14 Page 111 Export Classification C ECCN EAR99 Figure 5 5 Spiral Bevel Gears Serial Numbers 212_MM_05_0010 ...

Страница 135: ...ON COAST SIDE PATTERN VERY LIGHT LOCATED AT ONE OR TWO POSITIONS NOT ACCEPTABLE DETACHED STRIKE MARKS USUALLY ONE PER TOOTH USUALLY ON ONE OR MORE GROUPS OF 2 3 OR 4 TEETH TOE CONCAVE SIDE SCORED PATCH NOT ACCEPTABLE WILL BE ON ALL 62 TEETH 0 70 IN 17 78 mm APPROX 0 01 TO 0 04 IN 0 254 TO 1 016 mm ACCEPTABLE BAND OF BRIGHT MARKING ON ALL 62 TEETH 0 050 IN 1 270 mm APPROX PITCH DIA NORMAL GAP FROM ...

Страница 136: ...Export Classification C ECCN EAR99 Figure 5 6 Inspection of Spiral Bevel Gear Sheet 2 of 3 SPIRAL BEVEL GEAR 204 040 701 UNACCEPTABLE PATTERN REGISTRATION NO __________________________ SPIRAL BEVEL GEAR 204 040 701 UNACCEPTABLE PATTERN 212_MM_05_0005 ...

Страница 137: ...Export Classification C ECCN EAR99 Figure 5 6 Inspection of Spiral Bevel Gear Sheet 3 of 3 SPIRAL BEVEL GEAR 204 040 701 UNACCEPTABLE PATTERN SPIRAL BEVEL GEAR 204 040 701 UNACCEPTABLE PATTERN 212_MM_05_0006 REGISTRATION NO __________________________ ...

Страница 138: ...__ _________________________ NOTE Accomplish between 5 and 10 hours of flight after each installation Chapter 62 MAIN ROTOR 1 Torque check main rotor retaining nut 520 to 780 foot pounds 705 to 1057 Nm Chapter 64 2 Main rotor hub blade attachment bolts torque check nuts 260 to 300 foot pounds 353 to 407 Nm TAIL ROTOR 1 Torque check tail rotor retaining nut 900 inch pounds 101 69 Nm 2 Torque check ...

Страница 139: ...CN EAR99 Chapter 65 INTERMEDIATE GEARBOX Torque check intermediate gearbox retaining bolts 50 to 70 inch pounds 5 65 to 7 91 Nm SPECIAL INSPECTIONS 5 19 BETWEEN 5 AND 10 HOURS OF FLIGHT AFTER EACH INSTALLATION CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 140: ...nspection of fin spar caps P N 212 030 125 001 212 030 447 001 and 212 030 447 101 every 8 flight hours 2 This special inspection is not required if fin spar cap P N 212 030 447 117 has been installed as original equipment or in accordance with TB 212 00 184 3 Fin spar cap P N 212 030 447 117 can be identified by the presence of decals that identify the cold worked holes FIN SPAR CAP 212 030 125 0...

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Страница 142: ...ons after installation or initial inspection of hanger bearings NOTE All newly installed hanger bearings must contain a scribe or paint witness mark and will require an initial inspection ASB 212 95 95 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 identified by breakage of the witness marks Remove a...

Страница 143: ...fication C ECCN EAR99 3 Remove any hanger bearing from service where the witness marks indicate that the grease shield has moved SPECIAL INSPECTIONS 5 21 EACH 25 HOURS FOR THE NEXT FOUR INSPECTIONS CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 144: ...ours of operation Chapter 62 SWASHPLATE GIMBAL RING BOLTS NOTE This swashplate gimbal ring bolt special inspection is applicable to helicopters on Part A scheduled inspection program only The intent of this special inspection is included in the 25 hour 30 day inspection Part B Do not attempt to turn bolts or nuts Bolt rotation will fail loctite in joint and permit bolt wear The presence of black o...

Страница 145: ...inspection by cleaning exposed surfaces with denatured alcohol C 326 as per the BHT ALL SPM Wipe dry 2 Inspect grip surfaces for evidence of hairline cracks on grip barrels and upper and lower tangs exposed surfaces Pay particular attention to the lower tang lower surface from blade bolt bushing flange to the trailing and leading edge of the tang Figure 5 4 Chapter 62 ASB 212 08 130 MAIN ROTOR BLA...

Страница 146: ...rea to be inspected with a clean cloth C 516 soaked with isopropyl alcohol C 385 Wipe dry with a clean cloth C 516 NOTE Accomplish step 4 immediately after carrying out the above alcohol wipe Any potential cracks in the bond lines between doublers or grip plates will be indicated by the presence of excess alcohol bleeding out of an edge void The excess alcohol in the void will appear as a dark lin...

Страница 147: ...may indicate a possible edge void 5 Carry out a detailed visual inspection of the top and bottom inspection areas in the blade bolt area with a 10X power magnifying glass and a strong light source Inspect the leading edge and trailing edge sides of the blade at the blade bolt span station for evidence of cracks or dark lines in the grip plates going across the doublers Any cracks in the finish mus...

Страница 148: ...ction apply a light coat of preservative oil C 125 to all surfaces of blade Chapter 64 TAIL ROTOR HUB ASSEMBLY Detailed Visual Inspection 1 Flapping bearings 212 010 723 001 or 212 010 768 001 exposed outer races for cracks using a 3X magnifying glass Any crack is cause for immediate replacement of both bearings 2 Inspect tail rotor yoke 212 010 704 212 010 744 or 212 011 702 TAIL ROTOR STATIC STO...

Страница 149: ...y 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 or less is acceptable when polished out Replace any blade that has corrosion on the spar greater than 0 003 inch 5 If a nick scratch or dent is found visually inspect for crack using a 10X magnifying glass or higher and measure the depth of the d...

Страница 150: ... pad C 407 is permissible Corrosion on the spar 0 003 inch deep or less is acceptable when polished out Replace any blade that has corrosion on the spar greater than 0 003 inch 11 If a nick scratch or dent is found visually inspect for crack using a 10X magnifying glass or higher and measure the depth of the damage A digital optical micrometer is one tool that can be used for this measurement 12 R...

Страница 151: ...BHT 212 MM 1 Export Classification C ECCN EAR99 5 00 00 Figure 5 6A Tail Rotor Blade Detailed Inspection 212_MM_05_0006a Page 126B Rev 16 15 NOV 2018 ...

Страница 152: ...__ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 7 days in a corrosive environment and each 30 days in a noncorrosive environment Chapter 62 MAIN ROTOR BLADES 204 012 001 212 010 750 AND 212 015 501 Clean 1 Wash upper and lower surfaces with a solution of cleaning compound C 318 and water Rinse ...

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Страница 154: ...__ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish 50 flight hours after installation of components Chapter 53 TAILBOOM Torque check anti torque bellcrank support 212 001 706 001 101 attachment nuts 75 to 95 inch pounds 8 47 to 10 73 Nm Chapter 63 ROTOR BRAKE 1 Torque check brake assembly caliper attac...

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Страница 156: ...ch 50 hours of component operation Chapter 63 TRANSMISSION Detailed Visual Inspection 1 Transmission 212 040 001 115 119 123 and 127 remove internal filter and sump chip detector Visually inspect filter element and detector for metallic chips particles and contamination If contamination or debris is found investigate to determine cause Thoroughly clean and reinstall detector and filter Service tra...

Страница 157: ...mmediate replacement HELICOPTERS MODIFIED BY TB 212 91 138 TB 212 76 18 TB 212 86 92 TB 212 91 132 If Technical Bulletins 212 76 18 212 86 92 and 212 91 132 have not been incorporated the following listed inspection is mandatory 1 Inspect lift beam caps for cracks 2 Inspect L H spar cap fin for cracks 3 Inspect lift link fitting for cracks SPECIAL INSPECTIONS 5 25 EACH 50 HOURS OF COMPONENT OPERAT...

Страница 158: ...00 HOURS OF MAIN ROTOR BLADE OPERATION DELETED DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER NOTE The Each 100 Hours of Main Rotor Blade Operation special inspection has been moved to the Each 25 Hours of Flight Operation special inspection 26 JUN 2013 Rev 14 Page 133 134 ...

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Страница 160: ... _______________ _________________________ NOTE Accomplish each 100 hours or 12 months of transmission operation whichever occurs first Chapter 63 TRANSMISSION General Visual Inspection 1 Transmission oil system transmissions 212 040 001 115 119 123 and 127 with 10 micron external filter drain transmission oil system and replace filter Remove and inspect sump pump screen for debris If debris is fo...

Страница 161: ...nsmission oil Inspect and clean sump screen internal filter and chip If metallic chips or particles are found determine and correct cause 3 Replace filter element 4 Visually inspect the main case 204 040 353 023 for cracks in web above input quill bore using dye penetrant method if case has been previously reworked Any crack indication is cause for replacement of case SPECIAL INSPECTIONS 5 27 EACH...

Страница 162: ...__ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 100 hours or 12 months inspection of intermediate gearbox operation whichever occurs first INTERMEDIATE GEARBOX Detailed Visual Inspection Chapter 65 1 Torque check gearbox mounting bolts 2 Remove inspect and clean gearbox chip detector If metallic particles are found dete...

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Страница 164: ...TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 100 hours or 12 months inspection of tail rotor gearbox operation whichever occurs first TAIL ROTOR GEARBOX Detailed Visual Inspection Chapter 65 1 Torque check gearbox mounting nuts 2 Remove inspect and clean gearbox chip detector If metallic particles are found determine an...

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Страница 166: ...___________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 100 hours or 12 months inspection of battery system operation whichever occurs first BATTERY SYSTEM Detailed Visual Inspection Chapter 96 and BHT ALL SPM 1 Service battery in accordance with the battery manufactur...

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Страница 168: ...__ FACILITY _________________ _________________________ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish 100 hours inspection after each installation of tailboom Chapter 53 TAILBOOM Torque Torque check tailboom attachment bolts...

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Страница 170: ..._______________ NOTE Accomplish each 150 hours of starter generator P N 200SG119Q operation or more frequently if conditions warrant P N 200SG119Q refers to the starter generator without the QAD kit consisting of the mounting flange and ring clamp This special inspection is not applicable to starter generator P N 209 060 221 001 Chapter 71 1 Remove starter generator P N 200SG119Q 2 Inspect starter...

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Страница 172: ... 447 101 every 300 flight hours This special inspection is not required if fin spar cap P N 212 030 125 001 has not been modified by retrofit kit 212 704 087 ASB 212 01 73 1 This special inspection is not required if fin spar cap PN 212 030 447 117 has been installed as original equipment or in accordance with TB 212 00 184 Fin spar cap P N 212 030 447 117 can be identified by the presence of deca...

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Страница 174: ...300 hours or 12 months inspection of transmission operation whichever occurs first Chapter 63 TRANSMISSION Detailed Visual Inspection 1 Remove internal oil filter or internal full flow debris monitor as applicable transmission 212 040 001 059 131 141 191 and helicopters modified by TB 212 91 131 2 Inspect internal oil filter or internal full flow debris monitor If contamination chips or particles ...

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Страница 176: ... _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 300 hours or 3 months of driveshaft operation whichever occurs first Chapter 12 Chapter 63 BHT 212 CR O MAIN DRIVESHAFT 212 040 005 001 AND 011 1 Remove main driveshaft assembly 2 Visually inspect a...

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Страница 178: ...54 TAIL ROTOR CONTROL TUBE 212 001 055 101 AND BEARING DAS4 14A1 512 Chapter 67 1 Gain access to the tail rotor control tube P N 212 001 055 101 and bellcranks P N 212 001 705 001 and P N 212 001 759 101 2 Disconnect both ends of the tail rotor control tube P N 212 001 055 101 from the corresponding bellcranks 3 Without removing the tail rotor control tube visually inspect the flight control tube ...

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Страница 180: ... 150 hours or 600 start stop cycles which ever occurs first Main rotor grips P N 204 011 121 009 with 4000 hours or more Time In Service TIS are to be ultrasonically inspected every 400 hours or 1600 start stop cycles which ever occurs first Main rotor grips P N 204 011 121 009 with less than 4000 hours TIS do not require inspection until reaching 4000 hours Main rotor grips P N 204 011 121 121 wi...

Страница 181: ... service and a serviceable grip installed If the grip was inspected by a level I special the unserviceable grip is to be sent to a facility that has level II or III ultrasonic capability for further investigation All grips that have a crack indication and have been inspected by a level II or III are to be sent to Bell Helicopter Textron Refer to Information Letter IL GEN 04 98 for shipping instruc...

Страница 182: ...________ _________________________ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 500 hours or 6 months of blade inspection system if installed whichever occurs first Chapter 62 MAIN ROTOR BLADES Accomplish Blade Inspect...

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Страница 184: ...n TRANSMISSION ASSEMBLY 212 040 001 115 119 123 AND 127 Inspect 1 Remove input pinion quill assembly and No 2 hydraulic pump drive quill from transmission main case Dimensionally inspect input pinion quill bore diameter of main case for out of round condition Input quill bore shall be 6 7521 inches 171 5033 mm and maximum out of round condition maximum diameter minimum diameter shall be 0 0030 inc...

Страница 185: ...required 3 Inspect main input driven spiral bevel gear P N 204 040 701 003 as follows a Utilizing transmission case input quill port inspect all 62 teeth of the main input driven spiral bevel gear convex side for unsatisfactory conditions such as scoring hard lines nicks dents chipping metal deformation etc NOTE Inspection mirrors and a suitable light are required Turn rotor slowly to permit inspe...

Страница 186: ...E Accomplish each 600 hours of component operation or 6 months whichever occurs first No Non Destructive Inspection NDI required BHT 212 CR O Chapter 65 TAIL ROTOR DRIVESHAFT COUPLINGS 1 Remove tail rotor driveshaft assemblies NOTE Disassemble flexible couplings only to the extent necessary to remove old grease and repack 2 Clean visually inspect and repack tail rotor hanger assembly flexible coup...

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Страница 188: ...____ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 600 hours or 12 months of main driveshaft operation whichever occurs first No Non Destructive Inspection NDI required MAIN DRIVESHAFT 212 040 005 003 007 AND 103 Chapter 63 1 Remove main driveshaft NOTE Disassemble driveshaft only to the extent ...

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Страница 190: ...____________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish the following inspection each 600 hours or 12 months whichever occurs first The following inspection is not required for helicopters equipped with IFR Kit P N 212 706 106 MAGNETIC BRAKE ASSEMBLY P N 204 001 376 003 ASB 212 17 157 1 Perform a detailed visual in...

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Страница 192: ..._____________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish the following inspection each 600 hours or 12 months whichever occurs first The following inspection is not required if the discharge tubes 212 060 921 101 and 212 060 921 102 are installed in accordance with ASB 212 12 146 FIRE EXTINGUISHER DISCHARGE TUBES P N 212 0...

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Страница 194: ..._______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 1000 hours of component operation Chapter 29 HYDRAULIC ACCUMULATORS 1 Remove hydraulic accumulators BHT 212 CR O 2 Disassemble clean and visually inspect for corrosion and damage 3 Replace any unserviceable parts 4 Reassemble hydraulic accumulators Chapter 29 5 Install hydraulic accumul...

Страница 195: ...164 Rev 14 26 JUN 2013 Export Classification C ECCN EAR99 Chapter 79 5 Install oil cooler blowers SPECIAL INSPECTIONS 5 41 EACH 1000 HOURS OF COMPONENT OPERATION CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 196: ... 212 001 060 001 and 212 076 151 001 003 005 007 009 011 Supersedes ASB 212 76 6 ASB 212 76 6 Flight Control Tube Assemblies are identified by the following sub assemblies 204 001 957 001 contains tube assembly 204 001 957 003 205 001 017 001 contains tube assembly 205 001 017 003 205 001 017 007 contains tube assembly 205 001 017 009 212 001 051 001 contains tube assembly 212 001 051 005 212 001 ...

Страница 197: ...inspect external surfaces of control tubes for mechanical damage and or corrosion Refer to the BHT 212 CR O manual for limits d If serviceable coat the control tube threaded area with corrosion preventive compound C 101 reinstall clevis into control tube and adjust to recorded length 2 Inspect P N 204 001 957 001 205 001 017 001 and 007 212 001 051 001 212 001 060 001 control tubes as follows a Us...

Страница 198: ...Inspect ears by dye penetrant method Replace horn or fitting if any cracks are evident BHT 212 CR O b Inspect elevators for general condition cracks and corrosion Repair inboard rib if any cracks exist The inboard rib shall be replaced if any cracks extend into rib flange SPECIAL INSPECTIONS 5 42 FIRST 1000 HOURS OF COMPONENT TIME AND EACH 3000 HOURS THEREAFTER OF COMPONENT TIME CONT DATA REFERENC...

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Страница 200: ...__ NOTE Accomplish each 1000 hours or 12 months of main rotor blade operation whichever occurs first Chapter 62 MAIN ROTOR BLADES Clean and Inspect 1 Clean blade from an area starting at butt end of blade to several inches outboard of doublers on both upper and lower surfaces using aliphatic naphtha C 305 or equivalent NOTE Inspection may be accomplished with blades installed on main rotor hub ass...

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Страница 202: ...N ROTOR HUB PINS 204 012 104 003 005 AND INBOARD STRAP FITTINGS 212 010 103 005 007 BHT 212 CR O 1 Remove the four pins and two inboard strap fittings from the main rotor hub assembly 2 Inspect pins and inboard strap fittings by magnetic particle method 3 Magnetic particle indication interpreted as cracks are not acceptable and the pin or inboard strap fitting must be scrapped 4 If any strap pins ...

Страница 203: ... BHT ALL SPM 3 Perform a magnetic particle inspection 4 Install drag brace assemblies BHT 212 CR O MAIN ROTOR HUB GRIP 204 011 121 ALL Detailed Visual Inspection 1 Prepare both main rotor grip tangs for inspection by cleaning exposed surfaces with denatured alcohol C 326 as per BHT ALL SPM Wipe dry 2 Inspect grip surfaces for evidence of hairline cracks on upper and lower tangs exposed surfaces Pa...

Страница 204: ...Noted gap greater than the maximum permitted requires bushing to be replaced 5 Fit a blade bolt through both bushings simultaneously bolt should be able to be turned with the fingers If this cannot be accomplished refer to BHT 212 CR O Chapter 62 for further inspection requirements 6 Inspect buffer pads on tang inner surfaces for delamination Any delamination will require buffer pad replacement Fi...

Страница 205: ...5 7 Inspection of Main Rotor Hub Grip 1200 Hours 24 Months 212_MM_05_0007 GRIP 204 011 121 INSPECT BUFFER PAD FOR DELAMINATION IF INSTALLED AREA TO BE INSPECTED UPPER AND LOWER TANGS ALL EXPOSED SURFACES AREA TO BE INSPECTED GRIP BARREL LEADING AND TRAILING SIDES EXPOSED SURFACE 009 GRIP ONLY ...

Страница 206: ...RS OF MAIN ROTOR HUB PIN OPERATION DELETED DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER NOTE The Each 1200 Hours of Main Rotor Hub Pin Operation special inspection has been moved to the 1200 Hour 24 Months of Component Operation special inspection 26 JUN 2013 Rev 14 Page 175 176 ...

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Страница 208: ..._________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish the deflection check of the High Forward Crosstubes assemblies 205 050 403 031 and 412 050 046 101 at every 12 months or 2500 landings whichever occurs first HIGH FORWARD CROSSTUBES 205 050 403 031 AND 412 050 04...

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Страница 210: ..._________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish the fluorescent penetrant inspection of the High Forward Crosstubes assemblies 205 050 403 031 and 412 050 046 101 at every 12 months or 5000 landings whichever occurs first HIGH FORWARD CROSSTUBES 205 050 403 031 AND 41...

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Страница 212: ...________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish each 24 months of flight control system bolt operation Chapter 67 FLIGHT CONTROL SYSTEM BOLTS NOTE Refer to Chapter 4 for retirement life of flight control system bolts Inspect 1 Remove the following flight control bolts a Two fixed swashplate to right and left cyclic boost tube bolts P N 20 057 5 ...

Страница 213: ...ve link bolts P N 20 057 8S69D n Two scissors 204 011 406 pivot bolts P N 20 057 8S90D o Two stabilizer bar pivot bolts P N 20 057 10S27D or 20 057 10S29D p Three hydraulic cylinder to lower support bolts P N 212 001 304 003 or 212 001 323 001 q Two scissors 212 010 407 pivot bolts P N 212 010 411 005 or 212 010 411 003 001 ASB 212 89 56 r Two stabilizer bar damper tube to damper wing shaft bolts ...

Страница 214: ...pter 67 4 Apply corrosion preventive compound C 104 to shanks of bolts only and install bolts 5 After bolts have been installed and nuts torqued and safetied coat head of bolt nuts and lockwire with corrosion preventive compound C 101 SPECIAL INSPECTIONS 5 46 EACH 24 MONTHS OF FLIGHT CONTROL SYSTEM BOLT OPERATION CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER 26 JUN 2013 Rev 14...

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Страница 216: ...__ SIGNATURE _______________ _________________________ NOTE Accomplish each 3000 hours of listed component operation MAIN ROTOR MAST 204 040 366 021 AND 212 540 002 105 NOTE Mast assembly 204 040 366 021 installed in transmission prior to 212 040 001 059 141 with no top case chip detector overhaul interval is 2500 hours BHT 212 CR O Remove mast assembly from transmission and inspect inner and oute...

Страница 217: ... fretting and wear c Planetary component removal 1 Remove 204 040 360 upper planetary assembly and 204 040 117 adapter as an assembly 2 Remove M27426 1220C retaining ring and 204 040 117 adapter from 204 040 360 planetary assembly Do not disassemble 204 040 360 planetary assembly 3 Remove 204 040 337 liner and 204 040 135 bearing as an assembly Do not disassemble 4 Remove 205 040 231 ring gear ass...

Страница 218: ...ot diameter of 205 040 231 ring gear for fretting and wear Visually inspect upper and lower gear teeth contact patterns for evidence of pitting scoring wear or damage BHT 212 CR O f Visually inspect upper sun gear teeth for wear damage and contact pattern BHT 212 CR O g Disassemble 204 040 784 lower planetary to remove 204 040 785 spider BHT ALL SPM 1 Magnetic particle inspect 204 040 785 spider 2...

Страница 219: ...e of 205 040 245 bearing set for alignment NOTE If index marks indicate movement between gear and inner race of bearing set remove 204 040 701 gear 204 040 357 plate 204 040 348 shim 205 040 245 bearing set and 204 040 350 shim Visually inspect inside diameter of 205 040 245 bearing set for signs of spinning Visually inspect 205 040 245 bearing journal on 204 040 701 gear for sign of fretting Insp...

Страница 220: ...essive wear scoring pitting and contact pattern Visually inspect vibro etched index marks on 204 040 700 pinion and 214 040 118 bearing set for alignment Inspection may be accomplished with input quill installed by viewing pinion shaft and bearing inner race between teeth and main case NOTE If index marks indicate rotational movement between pinion and inner race of bearing set 212 040 263 quill s...

Страница 221: ...ess to accessory drive and sump gears Visually inspect accessory case input quill gear 212 040 150 005 and tail rotor drive quill gear 212 040 151 009 for general condition and wear pattern BHT 212 CR O 10 Assemble transmission SPECIAL INSPECTIONS 5 47 EACH 3000 HOURS OF COMPONENT OPERATION CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER ...

Страница 222: ...____ HELICOPTER S N __________ _________________________ REGISTRY NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish at 10 000 hours total airframe time and each 300 hours or 12 months whichever occurs first thereafter MAIN BEAM CAP This inspection is not required after main beam cap 205 0...

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Страница 224: ...ragraph 5 50 through paragraph 5 56 2 If overhaul evaluation is specified complete both the conditional inspection and normal inspection procedures as applicable for that component listed in BHT 212 CR O manual 3 If applicable conditional inspection does not provide complete information on a specific type of incident or if any doubt exists as to the serviceability of the helicopter of related comp...

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Страница 226: ...complish inspection after hard landing AFTER HARD LANDING NOTE Evaluate components removed from a helicopter following a hard landing as an interrelated group Make entries in component records of each removed component 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 which ground impact of heli...

Страница 227: ...evidence of hard rotor hub contact sufficient enough to yield or deform mast e Inspect mast area around pylon mount for loose rivets or other damage f 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 it is reasonably certain a true hard landing did not occur For helicopters on the...

Страница 228: ...veshaft b Perform a thorough visual inspection of 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 Tail rotor blades 4 Tail rotor hub ASB 212 96 100 and ASB 212 96 101 NOTE Inspect trunnion assembly 212 010 738 or flapping stop 212 011 713 for yielding as noted in Chapter 64 to determi...

Страница 229: ...e a complete inspection using a 10X magnifying glass of pylon support 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 link lift link attachment fittings and lift beam for cracks and other evidence of damage Remove lift link and replace with like serviceab...

Страница 230: ... tubes bellcranks bellcrank supports and for damaged control system bearings Particular attention should be given to pylon controls lower cylinder attachment support fitting and adjacent airframe structure l Pressurize hydraulic systems and check for leaks interference binding and satisfactory operation m Inspect fuel oil and pneumatic system for damage Make engine ground run and visually check fu...

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Страница 232: ...TAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE To be accomplished after a main rotor blade or tail rotor blade strike or any drive system failure that inhibits free rotation of drive system AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE NOTE If the blade strike or rotating system torque spike is the result of crash damage or resu...

Страница 233: ...lade replacement defined as removal for repair or scrap is considered sudden stoppage When sudden stoppage occurs inspect helicopter and replace components as follows 1 Perform a sudden stoppage inspection as follows NOTE If sudden stoppage inspection is the result of a tail rotor strike or main rotor blades striking the tail rotor driveshaft comply with step g through step n a Main rotor blades 1...

Страница 234: ...f the following discrepancies in step a through step f are found swashplate assembly stabilizer bar assembly and scissors and sleeve assembly shall be removed and an overhaul evaluation performed a Severe main rotor blade damage sufficient to require replacement b Pitch horn failure c Yielded stabilizer bar tube d Control tube buckled or broken e Transmission main support case mounting leg broken ...

Страница 235: ...n rotor hub due to the main rotor blades striking a foreign object c Damage or shearing of main rotor mast d Seizure of drive system components NOTE The transmission and mast assembly must be evaluated for serviceability as a set when removed for inspection requirements due to sudden stoppage Inspect in accordance with the BHT 212 CR O manual ensuring both conditional and normal inspections are ac...

Страница 236: ... other similar circumstance the hanger assemblies to which the damaged shaft was attached shall be scrapped If a tail rotor driveshaft fails as a result of torsional overload all hanger assemblies and shafts shall be scrapped BHT 212 CR O 2 If inspection reveals no damage that would render hanger assemblies non repairable hanger assemblies shall have an overhaul evaluation performed Make an entry ...

Страница 237: ...n rotor or main rotor transmission tail rotor hub and blade assembly may remain in service provided there is no visible external damage If visible damage is noted on tail rotor hub and blade assembly an overhaul of the tail rotor hub shall be performed Make an entry in component records to show reason for removal was sudden stoppage b If sudden stoppage originated at tail rotor driveshaft intermed...

Страница 238: ...d the tail rotor rotating control may remain in service Replace all tail rotor rotating control bolts If damage to the tail rotor rotating controls is found perform an overhaul of the tail rotor rotating controls Make an entry in component record to show that reason for removal was sudden stoppage k Tail rotor gearbox 1 Remove tail rotor gearbox Check for cracks sheared or bent attaching studs and...

Страница 239: ...smission sump case assembly 2 Inspect output quill pinion for unusual load patterns on both sides of teeth If no damage is found reinstall quill Transmission may be retained in service BHT 212 CR O 3 If tail rotor quill reveals discrepancies remove transmission and perform an overhaul evaluation Make an entry in component record to show reason for removal was sudden stoppage n Reinstall or replace...

Страница 240: ...________ NOTE Accomplish inspection after overspeed AFTER OVERSPEED NOTE Components 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 of other drive system components removed for evaluation Overspeed is defined as any incident in which 110 main rotor R...

Страница 241: ...lades to an authorized blade repair station Make an entry in component record to show reason for removal was overspeed Include amount of overspeed and duration if known d Tail rotor hub and blades 1 Remove tail rotor hub and blade assembly 2 Remove tail rotor blades 3 Replace tail rotor blade retention bolts e Tail rotor blades BHT 212 CR O 1 Perform major overspeed inspection of tail rotor blades...

Страница 242: ...s 7 Tail rotor driveshaft hangers 8 Stabilizer bar 9 Swashplate 10 Scissors and sleeve 11 Tail rotor hub g Install a serviceable main rotor hub and blade assembly Install serviceable tail rotor blades Balance and install tail rotor hub and blade assembly CONDITIONAL INSPECTIONS 5 52 AFTER OVERSPEED CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER 26 JUN 2013 Rev 14 Page 207 208 ...

Страница 243: ......

Страница 244: ...s removed from a helicopter for evaluation following an overtorque 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 Overtorque is defined as any incident in which torsional loads are introduced into the helicopter dynamic system in excess of established limit...

Страница 245: ... b Main rotor hub c Tail rotor hub d Intermediate gearbox Check gearbox for security and retorque retaining bolts e Tail rotor gearbox Check gearbox for security and retorque retaining nuts f Tail rotor driveshafts g Tail rotor driveshaft hangers h Stabilizer bar assembly i Swashplate j Scissors and sleeve assembly k Main driveshaft CONDITIONAL INSPECTIONS 5 53 AFTER OVERTORQUE CONT DATA REFERENCE...

Страница 246: ...appear normal and there is no evidence of internal failure return helicopter to service Operate normally for 5 hours and then check chip detector s and internal filter or full flow debris monitor If no metal particles are found indicating internal failure normal scheduled inspection intervals may then be followed If metal particles are present prior to or at the 5 hour check or if there is any evi...

Страница 247: ...de amount of overtorque and duration if known 1 Transmission 2 Main driveshaft 3 Main rotor hub 4 Mast 5 Perform thorough visual inspection of other components outlined in step 2 b Remove fifth mount bolts and remove fifth mount Perform a thorough inspection of bolts and fifth mount support Check for bent bolts and bent fifth mount support Check for bolt hole alignment between transmission and fif...

Страница 248: ...TALL OR SURGE NOTE Discuss circumstances of reported compressor stall with pilot if possible Determine N1 GAS PROD speed at which reported stall occurred Check helicopter and engine logs for any pertinent history Engine compressor stall or surge is characterized by a sharp rumble or a series of loud sharp reports severe engine vibration and a rapid rise in Interturbine Temperature ITT depending on...

Страница 249: ... reveal cause of surge perform a hot end inspection in accordance with Pratt Whitney Canada PT6T 3 3B Maintenance Manual 2 Power train a If compressor stall occurs below 85 N1 GAS PROD speed comply with step b and step c b Remove magnetic chip detectors from transmission intermediate gearbox and tail rotor gearbox Inspect for metal particles c If no evidence of damage is found on tailboom pylon an...

Страница 250: ...or there is other damage that would render gearbox unserviceable replace gearbox with a like serviceable item h Remove tail rotor drive quill from transmission and inspect gear teeth for damage with a 10X magnifying glass If there is no indication of scoring or scuffing and there is no other damage that would render transmission unserviceable it is suitable for continued use If gear teeth are scor...

Страница 251: ...eason for removal was compressor stall 3 Airframe a Check tailboom fin for evidence of damaged skin panels and or structure and rivets for looseness and or sheared heads If inspection shows no indication of damage return helicopter to flight status If positive evidence of damage is found comply with step b through step e b Remove skin from tailboom fin adjacent to tail rotor gearbox mounting Inspe...

Страница 252: ...d during inspection in step b through step d cannot be repaired by standard procedures replace discrepant assembly CONDITIONAL INSPECTIONS 5 54 AFTER ENGINE COMPRESSOR STALL OR SURGE CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER 26 JUN 2013 Rev 14 Page 217 218 ...

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Страница 254: ... STRIKES NOTE In all instances in the following inspections if significant damage has been found in any area inspection shall be expanded in those areas until it extends beyond zone of damage Any damage found anywhere on helicopter shall be recorded in detail and copies of these records shall be provided along with any component returned for overhaul to assist overhauling facility in evaluating co...

Страница 255: ...or inspection BHT 212 CR O 1 Disassemble to the same extent required for coupling Repack and clean couplings 2 Visually inspect couplings for any evidence of arc burning or pitting Pay special attention to tips roots and profiles of male and female coupling teeth Any evidence of arc burning or pitting is cause for rejection d Remove tail rotor output coupling for inspection BHT 212 CR O 1 Disassem...

Страница 256: ...rs f Inspect tail rotor blades and hub Scrap blades if indications of burns or debonding are present Remove tail rotor hub for overhaul Tag hub stating lightning strike as reason for removal Chapter 65 g Remove and inspect tail rotor gearbox chip detector and intermediate gearbox chip detector h If the tail rotor blades tail rotor hub or tail rotor output coupling exhibit evidence of damage which ...

Страница 257: ...onnections for arcing burns 3 If indications of arcing or burning are present overhaul main rotor hub and drive assembly Replace affected pitch change link including attaching hardware 4 If no indications are found reassemble main rotor hub 4 Prior to first flight after a suspected or confirmed lightning strike verify proper function of all drive system component chip detectors as follows a Remove...

Страница 258: ...5 inch 12 7 mm of item being checked and point it directly at item If any items or components have a reading greater than 1 gauss those items shall be degaussed NOTE Do not test chip detectors for magnetization If transmission or gearbox magnetic readings are greater than 1 gauss near chip detector remove chip detector from housing and repeat test c Remove and bench test voltage regulator s Operat...

Страница 259: ...es b Check fixed controls and support system components for possible arcing damage Bearings in rod ends bellcranks and supports should be most susceptible to arcing damage Check bearings for smooth rotation Visibly inspect attaching hardware of support for signs of lightning damage damaged finish and or burns If damage is evident remove supports and inspect mounting holes and mating surfaces for a...

Страница 260: ...pecifically identified above but are suspect shall be noted in maintenance log and shall be reinspected prior to next 100 hours of flight CONDITIONAL INSPECTIONS 5 55 AFTER LIGHTNING STRIKES CONT DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER 26 JUN 2013 Rev 14 Page 225 226 ...

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Страница 262: ...Y NO ____________ _________________________ TOTAL TIME _______________________________________ SIGNATURE _______________ _________________________ NOTE Accomplish inspection after engine combining gearbox clutch nonengagement misengagement or in flight slippage AFTER ENGINE COMBINING GEARBOX CLUTCH NONENGAGEMENT MISENGAGEMENT IN FLIGHT SLIPPAGE NOTE A nonengaged engine is indicated by near zero to...

Страница 263: ...assembly 2 Utilizing rotor brake quill port opening inspect all 62 teeth of main spiral bevel gear convex side for unsatisfactory conditions such as scoring hard lines nicks dents chipping metal deformation etc Inspect all 62 teeth on spiral bevel gear concave side Refer to Figure 5 6 for unacceptable conditions of spiral bevel gear NOTE Inspection mirrors and a suitable light are required Turn ro...

Страница 264: ...l leaks are present at rotor brake quill assembly c Perform inspection in accordance with compressor stall or surge inspection paragraph 5 52 except drive train shall be inspected as follows 1 Visually inspect main rotor mast and controls for damage If signs of yielding are evident transmission and mast assembly and any other damaged components shall be replaced 2 Visually inspect tail rotor drive...

Страница 265: ...ox but tail rotor driveshafts are serviceable gearbox es that are not serviceable shall be replaced 3 In flight clutch slippage NOTE If clutch slippage is confirmed or suspected proceed as follows Pratt Whitney Canada PT6T 3 3B Maintenance Manual a Combining gearbox shall be removed and inspected in accordance with Pratt Whitney Canada PT6T 3 3B Maintenance Manual b Inspect spiral bevel gear in ac...

Страница 266: ... IS NOT COVERED IN THIS SCHEDULE REFER TO APPLICABLE SERVICE INSTRUCTIONS FOR KIT COMPONENTS SCHEDULE NOTE Refer to paragraph 5 1 for information on inspection and overhaul tolerance NOTE Neither assignment of a time period for overhaul of a component or failure to assign a time period for overhaul of a component constitutes a warranty of any kind The only warranty applicable to helicopter and any...

Страница 267: ...sion 212 040 001 115 119 123 and 127 1000 hours Transmission 212 040 001 131 1500 hours Transmission 212 040 001 059 137 and Subsequent 6000 hours Transmission 212 540 002 103 6000 hours Quill Assembly Auxiliary Equipment 212 040 703 105 1000 hours Intermediate Gearbox Assembly 212 040 003 007 3000 hours Intermediate Gearbox Assembly 212 040 003 023 5000 hours Intermediate Gearbox Assembly 212 540...

Страница 268: ...000 hours Mast Assembly 212 540 002 105 5000 hours Tail Rotor Driveshaft Hanger Assembly 212 040 600 001 3000 hours HYDRAULIC Cylinder Assembly Servo Actuator 212 076 004 003 1000 hours On condition Cylinder Assembly Servo Actuator 212 076 004 005 On condition Cylinder Assembly Flight Control 212 076 005 007 2500 hours POWER PLANT Engine Combining Reduction Gearbox PT6T3 3B 3500 hours Starter Gene...

Страница 269: ...quired at 3000 hours and overhaul is 6000 hours Special inspection is required at 3000 hours and overhaul is 5000 hours If mast assembly 204 040 366 021 is installed in transmission 212 040 001 115 123 and 131 mast assembly TBO is 2500 hours If cylinders have Greene Tweed type seals installed overhaul is conditional Cylinders with assembly date of April 30 1974 or later were fitted with Greene Twe...

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