MAINTENANCE MANUAL VOLUME 1 GENERAL INFORMATION

Name of New Operator _______________________________________________________ Future Publications to be mailed to this address: Address ____________________________________________________________________ City _______________________________________________________________________ State/Province _______________________________________________________________ Zip/Postal Code _____________________________________________________________ Country ____________________________________________________________________ Fax No. ___________________________ Telephone No. ____________________________ E-mail Address ______________________________________________________________ Register for access to electronic publications at www.bellhelicopter.net Export Classification C, ECCN EAR99 TAPE HERE From NO POSTAGE NECESSARY IF 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 BHT-214ST-MM SPARE PARTS WARRANTY ONE YEAR/1,000 HOURS PRORATED WARRANTY AND REMEDY: Seller warrants each new helicopter part or helicopter part reconditioned by seller to be free from defect in material and workmanship under normal use and service and if installed on Bell model helicopters. Seller’s sole obligation under this warranty is limited to replacement or repair of parts which are determined to Seller’s reasonable satisfaction to have been defective with 1,000 hours of operation or one (1) year after installation, whichever occurs first and reimbursement of reasonable freight charges. After 200 hours of use, there will be a prorated charge to the Purchaser for replacement parts (prorating the hours of total use against the then applicable part life or 2,000 hours, whichever is the lesser). Defective parts must be reported in writing to the Seller’s Warranty Administration within 90 days of being found defective. Replacement of parts may be with either new or reconditioned parts, at Seller’s election. Warranty adjustment is contingent upon the Purchaser complying with the Warranty Remedies as described in the Commercial Warranty Information brochure and the Seller’s Warranty Administration disposition instructions for defective parts. Failure to comply with all of the terms of this paragraph may, at Seller’s sole option, void this warranty. NOTE: Parts, components and assemblies of all new helicopters may have been restored or reworked due to mars, blemishes, dents or other irregularities during the manufacturing process. Such restoration and/or rework is permitted under Seller’s approved manufacturing and engineering processes and guidelines. The restoration and/or rework so completed does not render such items defective in material or workmanship. THIS WARRANTY IS GIVEN AND ACCEPTED IN PLACE OF (i) ALL OTHER WARRANTIES OR CONDITIONS, EXPRESS OR IMPLIED, INCLUDING BUT NOT LIMITED TO THE IMPLIED WARRANTIES OR CONDITIONS OF MERCHANT ABILITY AND FITNESS FOR A PARTICULAR PURPOSE AND (ii) ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR REMEDY IN CONTRACTOR IN TORT (DELICT), INCLUDING PRODUCT LIABILITIES BASED UPON STRICT LIABILITY, NEGLIGENCE, OR IMPLIED WARRANTY IN LAW. This warranty is the only warranty made by Seller. The Purchaser’s sole remedy for a breach of this warranty or any defect in a part is the repair or replacement of helicopter parts and reimbursement of reasonable freight charges as provided herein. Seller excludes liability, whether as a result of a breach of contract or warranty, negligence or strict product liability, for incidental or consequential damages, including without limitation, damage to the helicopter or other property, costs and expenses resulting from required changes or modifications to helicopter components and assemblies, changes in retirement lives and overhaul periods, local customs fees and taxes, and costs or expenses for commercial losses or lost profits due to loss of use or grounding of helicopters or otherwise. Seller makes no warranty and disclaims all liability in contract or in tort (delict), including, without limitation, negligence 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 altered outside Seller’s factory in any way so as, in Seller’s judgment, to affect its stability, safety or reliability, or which has been subject to misuse, negligence or accident, or which has been installed in any aircraft which has been destroyed unless that helicopter has been rebuilt by Bell. A list of destroyed aircraft is obtainable from Bell Product Support. Repairs and alterations which use or incorporate parts and components other than genuine Bell parts or parts approved by Bell for direct acquisition from sources other than Bell itself are not warranted by Bell, and this warranty shall be void to the extent that such repairs and alterations, in Seller’s sole judgment, affect the stability, safety or reliability of the helicopter or any part thereof, or damage genuine Bell or Bell-approved parts. No person, corporation or organization, including Bell Customer Service Facilities, is authorized by Seller to assume for it any other liability in connection with the sale of its helicopters and parts. NO STATEMENT, WHETHER WRITTEN OR ORAL, MADE BY ANY PERSON, CORPORATION OR ORGANIZATION, INCLUDING BELL CUSTOMER SERVICE FACILITIES MAY BE TAKEN AS A WARRANTY NOR WILL IT BIND SELLER. Seller makes no warranty and disclaims all liability with respect to components or parts damaged by, or worn due to, corrosion. Seller makes no warranty and disclaims all liability for consumables (wear items) which are defined as items required for normal and routine maintenance or replaced at scheduled intervals shorter than the warranty period. “Consumables” include but are not limited to engine and hydraulic oil, oil filters, packings and o-rings, anti-corrosion and/or sealing compounds, brush plating material, nuts, bolts, washers, screws, fluids, compounds, and standard aircraft hardware that is readily available to aircraft operators from sources other than Seller. All legal actions based upon claims or disputes pertaining to or involving this warranty including, but not limited to, Seller’s denial of any claim or portion thereof under this warranty, must be filed in the courts of general jurisdiction of Tarrant County, Texas or in the United States District Court for the Northern District of Texas, Ft. Worth Division located in Ft. Worth, Tarrant County, Texas. In the event that Purchaser files such an action in either of the court systems identified above, and a final judgment in Seller’s favor is rendered by such court, then Purchaser shall indemnify Seller for all costs, expenses and attorneys’ fees incurred by Seller in defense of such claims. In the event Purchaser files such a legal action in a court other than those specified, and Seller successfully obtains dismissal of that action or transfer thereof to the above described court systems, then Purchaser shall indemnify Seller for all costs, expenses and attorneys’ fees incurred by Seller in obtaining such dismissal or transfer. January 2007 22 FEB 2013 Rev. 9 Warranty Export Classification C, ECCN EAR99 FAA APPROVED BHT-214ST-MM 4-00-00 Export Classification C, ECCN EAR99 TABLE OF CONTENTS Paragraph Chapter/Section Page Number Title Number Number CHAPTER 4 — AIRWORTHINESS LIMITATIONS SCHEDULE AIRWORTHINESS LIMITATIONS SCHEDULE 4-1 Airworthiness Limitations Schedule ............................................... 4-00-00 5 TABLES Table Page Number Title Number 4-1 Airworthiness Limitations Schedule .................................................................... 6 10 MAY 2018 Rev. 13 Page 1/2 FAA APPROVED BHT-214ST-MM 4-00-00 10 MAY 2018 Rev. 13 Page 3 Export Classification C, ECCN EAR99 214ST ALS Revision 13 (SIGNATURE) REVISION NO. DATE OF SIGNATURE FAA/ODA* SIGNATURE Basic Manual 4 January 1982 1 30 June 1982 2 30 August 1982 3 15 October 1982 Chapter 4 not affected 4 1 December 1982 5 – 8 Chapter 4 not affected 9 29 July 1983 10 – 14 Chapter 4 not affected 15 25 January 1984 16 4 May 1984 Chapter 4 not affected 17 15 June 1984 18 15 January 1985 19 28 May 1985 Not required – Temporary Revision 85-53 previously signed 20 3 September 1985 Chapter 4 not affected 21 15 April 1986 22 14 May 1987 BHT-214ST-MM FAA APPROVED 4-00-00 Page 4 Rev. 14 2 OCT 2018 Export Classification C, ECCN EAR99 23 5 February 1988 24 7 June 1988 25 12 January 1990 Reissue 26 May 1995 1 17 May 1996 Chapter 4 not affected 2 3 September 1996 Chapter 4 not affected 3 2 May 1997 Chapter 4 not affected 4 20 June 1997 5 14 May 2003 Chapter 4 not affected 6 20 May 2009 7 5 May 2011 * 8 – 11 Chapter 4 not affected 12 20 April 2015 13 10 MAY 2018 14 2 OCT 2018 REVISION NO. DATE OF SIGNATURE FAA/ODA* SIGNATURE FAA APPROVED BHT-214ST-MM 4-00-00 10 MAY 2018 Rev. 13 Page 5 Export Classification C, ECCN EAR99 AIRWORTHINESS LIMITATIONS SCHEDULE 4-1. AIRWORTHINESS LIMITATIONS SCHEDULE The Airworthiness Limitations Schedule is FAA approved and specifies maintenance required under paragraphs 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. WARNING A L L R E PA I R A N D O V E R H A U L PROCEDURES LIVES PUBLISHED BY B E L L H E L I C O P T E R T E X T R O N , INCLUDING COMPONENT RETIREMENT LIFE, ARE BASED SOLELY ON THE USE O F B E L L A P P R O V E D PA R T S A N D P R O C E S S E S . I F PA R T S O R P R O C E S S E S D E V E L O P E D O R APPROVED BY PARTIES OTHER THAN BELL HELICOPTER ARE USED, THEN THE DATA PUBLISHED OR OTHERWISE SUPPLIED BY BELL HELICOPTER ARE N O T A P P L I C A B L E . T H E U S E R I S WA R N E D T O N O T R E LY O N B E L L HELICOPTER DATA FOR PARTS AND PROCESSES NOT APPROVED BY BELL H E L I C O P T E R . A L L A P P L I C A B L E INSPECTIONS AND REPAIR METHODS M U S T B E O B TA I N E D F R O M T H E S U P P L I E R O F T H E PA R T S O R PROCESSES NOT APPROVED BY BELL HELICOPTER. BELL HELICOPTER IS NOT RESPONSIBLE FOR PARTS OR PROCE SSE S OTHER THA N THOS E WHICH IT HAS ITSELF DEVELOPED OR APPROVED. The mandatory airworthiness limitations schedule (Table 4-1) summarizes the mandatory maximum life, in hours, years or by Retirement Index Number (RIN) of components with a limited airworthiness life. Parts that are not on the schedule have an unlimited airworthiness life. Refer to the engine manufacturer's publications for the airworthiness limitations schedule of the engines and components (General Electric CT7-2A manuals). NOTE The airworthiness life or inspection interval for any part number contained in this schedule applies to all the successive dash numbers for that component unless it is otherwise specified. WARNING S O M E PA R T S A R E I N S TA L L E D A S O R I G I N A L E Q U I P M E N T O N B O T H M I L I TA R Y A N D C O M M E R C I A L H E L I C O P T E R S A N D M AY H AV E A LOWER AIRWORTHINESS LIFE AND/OR OVERHAUL SCHEDULE WHEN USED O N A M I L I TA R Y H E L I C O P T E R . I N A D D I T I O N , C I R C U M S TA N C E S SURROUNDING THEIR USE MAY CALL FOR OPERATION OF THE MILITARY H E L I C O P T E R O U T S I D E O F T H E A P P R O V E D C O M M E R C I A L F L I G H T ENVELOPE. CONSEQUENTLY, PARTS THAT HAVE BEEN USED ON MILITARY HELICOPTERS SHOULD NOT BE USED ON COMMERCIAL HELICOPTERS. CAUTION AIRWORTHINESS LIFE OF SOME KIT COMPONENTS MAY NOT BE COVERED I N T H I S S C H E D U L E . R E F E R T O APPLICABLE SERVICE INSTRUCTION ( S I ) O R M A I N T E N A N C E M A N U A L S U P P L E M E N T ( M M S ) F O R K I T COMPONENTS SCHEDULE. NOTE The airworthiness life given or the failure to give an airworthiness life to a component does not constitute a warranty of any kind. The only warranty applicable to the helicopter or any component is the warranty included in the Purchase Agreement for the helicopter or the component. BHT-214ST-MM FAA APPROVED 4-00-00 Page 6 Rev. 13 10 MAY 2018 Export Classification C, ECCN EAR99 The airworthiness lives given to the components and assemblies are determined by experience, tests, and the judgement of Bell Helicopter Texton engineers. The airworthiness lives and inspection intervals cannot be changed without the approval of the FAA. Prior to disposing of unsalvageable helicopter parts and materials, caution should be exercised to ensure that the parts and materials are disposed of in a manner that does not allow them to be returned for service. Refer to FAA Advisory Circular 21-38 for guidance on the disposal of unsalvageable aircraft parts and materials. Table 4-1. Airworthiness Limitations Schedule NOMENCLATURE PART NUMBER AIRWORTHINESS LIFE MAIN ROTOR HUB AND BLADE ASSEMBLY Blade Assembly 214-015-300-105 22,500 hours Yoke 214-010-105-001 2500 hours Yoke 214-010-105-111 2500 hours or 10 years in-service, whichever occurs first Bolt – Yoke/Spindle 214-010-183-101 1250 hours Bolt – Yoke/Spindle 214-010-261-101 1250 hours Bolt – Yoke/Spindle 214-010-262-103 2500 hours Trunnion 214-010-230-101 120,000 RIN Spindle 214-010-103-003 1250 hours Spindle 214-010-103-115 5000 hours Grip Assembly 214-010-104-113 2500 hours Grip Assembly 214-010-104-121 5000 hours Barrel, Drag Brace 214-010-192-101 10,000 hours Barrel, Drag Brace 214-010-120-107 2500 hours Clevis, Drag Brace 214-010-121-105 2500 hours Clevis, Drag Brace 214-010-193-101 10,000 hours Strap Fitting 214-010-115-001 2500 hours Strap Fitting 214-010-185-107 2500 hours Strap Fitting 214-010-189-103 2500 hours Strap 214-010-179-003 1250 hours or 24 months, whichever occurs first Pin 214-010-117-001 2500 hours Pillow Block Bearing Bolts 20-057-12-48D 17,000 RIN Pillow Block Bearing Bolts 20-057-12-50D 17,000 RIN 1 12 15 2 3 4 5 11 11 6 7 3 4 3 4 FAA APPROVED BHT-214ST-MM 4-00-00 2 OCT 2018 Rev. 14 Page 7 Export Classification C, ECCN EAR99 MAIN ROTOR CONTROLS Pitch Link Assembly 214-010-410-011 5000 hours Pitch Link Assembly 214-010-490-103 10,000 hours Scissors Assembly 214-010-506-105 10,000 hours Scissors Hub Assembly 214-010-505-101 10,000 hours Scissors Hub Assembly 214-010-505-109 10,000 hours Swashplate Outer Ring 214-010-503-105 5000 hours Collective Lever Assembly 214-010-474-109 1250 hours Collective Lever Assembly 214-010-492-105 15,000 hours Collective Lever Assembly 214-010-250-101 15,000 hours Collective Sleeve 214-010-411-001 5000 hours Collective Idler Link 214-010-558-101 10,000 hours Swashplate Inner Ring 214-010-402-113 5000 hours Swashplate Support 214-010-504-101 15,000 hours Drive Link Assembly 214-010-536-101 10,000 hours Housing 214-010-538-101 10,000 hours Hydraulic Actuator 214-076-161-101 10,000 hours Trunnion 214-010-539-101 10,000 hours Rod End Bearing 214-001-051-007 15,000 hours TAIL ROTOR HUB AND BLADES Blade Assembly 214-015-700-103 2500 hours Blade Assembly 214-015-700-111 4000 hours Blade Assembly 214-015-700-115 4000 hours Grip Plate Set 214-010-822-101 15,000 hours Yoke Assembly 214-010-702-107 5000 hours Yoke Assembly 214-011-802-101 5000 hours ELEVATOR AND CONTROLS Elevator Spar 214-021-101-111 7500 hours Elevator Assembly 214-021-100-103 12500 hours Elevator Assembly 214-021-100-104 12500 hours Elevator Assembly 214-021-100-105 12500 hours Elevator Assembly 214-021-100-106 12500 hours DRIVE SYSTEM Table 4-1. Airworthiness Limitations Schedule (Cont) NOMENCLATURE PART NUMBER AIRWORTHINESS LIFE 1 8 16 BHT-214ST-MM FAA APPROVED 4-00-00 Page 8 Rev. 14 2 OCT 2018 Export Classification C, ECCN EAR99 Main Rotor Mast 214-040-090-109 140,000 RIN Tail Rotor Mast 214-040-404-101 5000 hours ROTOR BRAKE QUILL Quill Bearing 204-040-424-103 600 hours NODALIZED PYLON Transmission Spindle 214-030-606-103 2500 hours or 50000 RIN Fore-and-aft Restraint 214-031-612-111 500 hours Fore-and-aft Restraint 214-031-612-115 On Condition Fore-and-aft Restraint 214-031-612-701 500 hours TRANSMISSION Upper Planetary Carrier 214-040-077-007 120,000 RIN Lower Planetary Spider 214-040-080-101 80,000 RIN Lower Planetary Spider 214-040-357-101 400,000 RIN POWER PLANT Engine CT7-2A Refer to GE Publication for retirement life of engine and components LANDING GEAR Beam Assembly (Left) 214-052-102-101 15,000 hours Beam Assembly (Right) 214-052-102-102 15,000 hours Beam Assembly (Left) 214-052-102-103 15,000 hours Beam Assembly (Right) 214-052-102-104 15,000 hours Beam Assembly (Left) 214-052-102-105 15,000 hours Beam Assembly (Right) 214-052-102-106 15,000 hours EMERGENCY FLOAT SYSTEM Hose Assembly 70-072V000A166 6 years Hose Assembly 70-072W000B124 6 years Hose Assembly 70-072W000C216 6 years Hose Assembly 70-072X000C196 6 years Hose Assembly 70-072Y000A124 6 years Hose Assembly 70-072Z000A236 6 years Hose Assembly 70-072Z000D202 6 years EMERGENCY FLOAT SYSTEM (CONT) Table 4-1. Airworthiness Limitations Schedule (Cont) NOMENCLATURE PART NUMBER AIRWORTHINESS LIFE 1 3 4 3 9 17 3 4 3 4 3 9 10 10 10 10 10 10 10 FAA APPROVED BHT-214ST-MM 4-00-00 2 OCT 2018 Rev. 14 Page 9 Export Classification C, ECCN EAR99 Hose Assembly 214-073-934-101 6 years Hose Assembly 70-072Z000E380 6 years FLOTATION SYSTEM Float Reservoir 222-325-021-101 15 years Float Reservoir 222-025-875-101 15 years LIFE RAFT SYSTEM Ejection Cylinder 6400-001 15 years Ejection Cylinder 44000-1 20 years FIRE PROTECTION Fire Extinguisher Cartridge 13083-5 6 years RESCUE HOIST Cable Cutter Cartridge 300078-1 5 years Cable Cutter Cartridge 42277-231 5 years Cable Cutter Cartridge 42315-281 5 years NOTES: Airworthiness limitation for part number listed applies to all successive dash numbers for that component unless otherwise specified. Dash numbers are defined as the last three numeric digits in a typical twelve-digit Bell part number (xxx-xxx-xxx-xxx). Suffixes (letters following the dash number) are for reference only. For reference only: Inactivated by ASB 214ST-85-32. RIN (Retirement Index Number) is the retirement life based on fatigue damage from normal helicopter lifts and takeoffs. New components will begin with an accumulated RIN of zero that will be increased as lifts and takeoffs are performed. Operators must record the number of lifts and takeoffs and increase the accumulated RIN accordingly. When the maximum RIN or retirement flight hours is reached, whichever occurs first, the component will be removed from service. Each takeoff or lift counts as 2 RIN. If logging, increase RIN count to 4. The 214-010-104-113, -117 grip assembly retirement life is 1250 hours when used with 214-010-115-001 strap fitting. The 214-010-104-113, -117 grip assembly retirement life is 2500 hours when used with 214-010-189-103 strap fitting, 214-010-190-101 liner, and 214-010-188-101 shim, and my remain in service for 2500 hours if the -115 -001 strap fitting was replaced with the -189 -103 strap fitting prior to 1250 hours. All tension-torsion straps must be retired after 24 months calendar time in service. In this application, calendar time in service begins when new straps installed in main rotor hub and blade assembly are subjected to powered rotation. At each tension-torsion strap replacement, remove scissors and sleeve driveplate and inspect splines for wear using 0.1728 inch (4.389 mm) diameter pins (Chapter 62). Table 4-1. Airworthiness Limitations Schedule (Cont) NOMENCLATURE PART NUMBER AIRWORTHINESS LIFE 1 10 10 14 14 14 14 13 13 13 13 1 2 3 4 5 6 7 BHT-214ST-MM FAA APPROVED 4-00-00 Page 10 Rev. 13 10 MAY 2018 Export Classification C, ECCN EAR99 Table 4-1. Airworthiness Limitations Schedule (Cont) NOTES: (CONT) Requires nut P/N 214-010-417-103. Each takeoff or lift counts as 1 RIN. If logging, increase RIN count to 2. For components flagged with this note, retirement life begins on initial installation and runs continuously regardless of the number of times the hoses may be removed and reinstalled. For reference only: Inactivated by ASB 214ST-88-47. The 214-010-105-001 M/R yoke life is reduced to 2500 hours per AD 86-12-06. For components flagged with this note, life is from date of manufacture, any combination of storage and in-service use. For components flagged with this note, life begins at manufacture date/first hydrostatic test date as marked on reservoir/cylinder. For components flagged with this note, in-service life begins the day the component is entered into service. In-service life only remains in effect while the component is installed on the helicopter. Per TB 214ST-98-158, the 10,000 hour life only applies against the lower barrel 41002418, 41005233, or 41005043 details. All other parts of the 214-076-161-101 servo assembly are unlimited life providing a 10,000 hour Time Between Overhaul (TBO) is maintained, reference Chapter 5 Component Overhaul Schedule. Reference AD 2013-19-05. 8 9 10 11 12 13 14 15 16 17 BHT-214ST-MM 5-00-00 22 FEB 2013 Rev. 9 Page 1 Export Classification C, ECCN EAR99 TABLE OF CONTENTS Paragraph Chapter/Section Page Number Title Number Number CHAPTER 5 — INSPECTIONS INSPECTIONS 5-1 General .......................................................................................... 5-00-00 3 5-2 Items Not Covered in the Inspection.............................................. 5-00-00 3 5-3 Crash Damage............................................................................... 5-00-00 4 5-4 Types of Inspections ...................................................................... 5-00-00 4 5-5 Definitions ...................................................................................... 5-00-00 5 5-6 Inspection and Overhaul Tolerance ............................................... 5-00-00 6 5-7 Maintenance Zones ....................................................................... 5-00-00 6 SCHEDULED INSPECTION 5-8 Scheduled Inspections................................................................... 5-00-00 13 5-9 A — Inspection (25 Hours/7 Days) ................................................ 5-00-00 15 5-10 B — Inspection (250 Hours)........................................................... 5-00-00 25 5-11 C — Inspection (500 Hours) .......................................................... 5-00-00 35 5-12 D — Inspection (1000 Hours/1 Year)............................................. 5-00-00 41 5-13 E — Inspection (5000 Hours/5 Years) ........................................... 5-00-00 47 SPECIAL INSPECTIONS 5-14 Special Inspections ........................................................................ 5-00-00 51 5-15 Daily ............................................................................................... 5-00-00 53 5-16 During first 5 Hours Flight Operation After Installation................... 5-00-00 55 5-17 Between 5 and 10 Hours Flight Operation After Installation .......... 5-00-00 57 5-18 Between 5 and 25 Hours Flight Operation After Installation .......... 5-00-00 59 5-19 Between 10 and 15 Hours Flight Operation After Installation ........ 5-00-00 61 5-20 Between 10 and 25 Hours Flight Operation After Installation or Adjustment ..................................................................................... 5-00-00 63 5-21 After 24 Hours................................................................................ 5-00-00 65 5-22 Each 100 Hours Flight Operation................................................... 5-00-00 67 5-23 Each 100 Hours Airframe Time or 90 Days ................................... 5-00-00 69 5-24 Each 250 Hours Flight Operation or 6 Months............................... 5-00-00 71 5-25 Each 250 Hours Flight Operation or 12 Months............................. 5-00-00 73 5-26 Each 500 Hours Flight Operation or 12 Months............................. 5-00-00 75 5-27 Each 1000 Hours Flight Operation................................................. 5-00-00 77 5-28 Each 1250 Hours Flight Operation or 12 Months........................... 5-00-00 79 5-29 Each 1250 Hours Flight Operation or 24 Months........................... 5-00-00 81 5-30 Each 2500 Hours Flight Operation................................................. 5-00-00 83 5-31 Each 180 Days or 6 Months........................................................... 5-00-00 85 5-32 Once a Year (Annually).................................................................. 5-00-00 87 5-33 Each 3 Years ................................................................................. 5-00-00 89 5-34 Each 5 Years ................................................................................. 5-00-00 91 BHT-214ST-MM 5-00-00 Page 2 Rev. 9 22 FEB 2013 Export Classification C, ECCN EAR99 TABLE OF CONTENTS (CONT) Paragraph Chapter/Section Page Number Title Number Number CONDITIONAL INSPECTIONS 5-35 Conditional Inspections.................................................................. 5-00-00 93 5-36 After Hard Landing......................................................................... 5-00-00 95 5-37 After Sudden Stoppage.................................................................. 5-00-00 101 5-38 After Overspeed............................................................................. 5-00-00 107 5-39 After Compressor Stall or Surge .................................................... 5-00-00 113 5-40 After Overtorque ............................................................................ 5-00-00 119 5-41 After Lightning Strike...................................................................... 5-00-00 123 COMPONENT OVERHAUL SCHEDULE 5-42 Component Overhaul Schedule..................................................... 5-00-00 127 FIGURES Figure Page Number Title Number 5-1 Major Zones ........................................................................................................ 7 5-2 Sub-major Zones ................................................................................................ 8 TABLES Table Page Number Title Number 5-1 Component Overhaul Schedule.......................................................................... 128 BHT-214ST-MM 5-00-00 22 FEB 2013 Rev. 9 Page 3 Export Classification C, ECCN EAR99 INSPECTIONS 5-1. GENERAL This chapter contains the requirements for the Scheduled Inspection, Special Inspection, Conditional Inspection, and the Component Overhaul Schedule. These inspection requirements constitute an approved inspection program designed and recommended by Bell Helicopter Textron for Model 214ST Series helicopters. They can be utilized by registered owners or operators who desire to develop a progressive inspection system to be used as part of the complete maintenance program. A written request for approval to use the progressive inspection system shall be submitted to the governing civil aviation authority having jurisdiction over the area in which the owner or operator is located. Relief from their requirements in this chapter can be requested through the local aviation authority. WARNING FAILURE TO CORRECT CONDITIONS S U C H A S , B U T N O T L I M I T E D T O , CORROSION, EROSION, MECHANICAL DAMAGE, OR OBVIOUS WEAR FOUND DURING A SCHEDULED INSPECTION C O U L D S E R I O U S L Y A FF E C T T H E AIRWORTHINESS OF THE HELICOPTER. 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 environmental conditions, helicopter use, etc. You can request changes to the requirements in this chapter through the local aviation authority. The inspection intervals and the Component Overhaul Schedule given in this chapter are applicable only to Bell Helicopter Textron approved parts. NOTE The time period given for the overhaul of a component (or the failure to give a time period for the overhaul of a component) does not constitute a warranty of any kind. The only warranty applicable to the helicopter or any component is the warranty included in the Purchase Agreement for the helicopter or the component. The Time Between Overhaul (TBO) and the inspection periods are determined through experience, tests, Lead-The-Fleet (LTF), or any other special programs and the judgement of Bell Helicopter Textron engineers. They are subject to change only by Bell Helicopter Textron or an approved airworthiness authority. Changes to the TBO will be introduced by either revision to the Maintenance Manual, Chapter 5 or a Technical Bulletin. Every calendar and hourly inspection is a thorough visual inspection to determine the airworthiness of the helicopter and the components. Qualified persons must do the inspections in accordance with quality standard aircraft practices and the applicable Maintenance Manuals. Bell Helicopter Textron considers that it is mandatory to obey all the applicable Alert Service Bulletins (ASB) and the Airworthiness Directives (AD). Component operating time records are necessary for components that have scheduled maintenance procedures that are different from those of the airframe. It is the owner/operator’s responsibility to keep the Historical Service Records for the applicable component and to do the necessary maintenance procedures. Before each inspection, remove or open the necessary cowlings, fairing, inspection doors, and panels. 5-2. ITEMS NOT COVERED IN THE INSPECTION This manual does not include the specific inspection intervals for some components such as the compass calibration and the pitot static test. These specific inspection intervals are given by your government regulatory authority. Refer to their requirements for these specific inspections. BHT-214ST-MM 5-00-00 Page 4 Rev. 9 22 FEB 2013 Export Classification C, ECCN EAR99 The owner/operator of the helicopter is responsible for the maintenance done on the helicopter. It is the owner/operator’s responsibility to: 1. Establish, maintain, and review the log books for discrepancies. 2. Make sure the Alert Service Bulletins (ASB), Airworthiness Directives (AD), and special inspections are done when they are required to be done. 3. Make sure the scheduled inspections, special inspections, and required tests for all of the installed kits are complied with. 4. Make sure all parts and components for which Historical Service Records are required have documented traceability to their original installation in the helicopter. 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 all of the maintenance that is done on the helicopter is done by an approved maintenance organization. The maintenance organization/person doing the maintenance is responsible for the quality of the maintenance done. The owner/operator may choose to ask the maintenance organization/person doing the maintenance to perform the tasks listed by prior arrangement through a separate formal agreement. 5-3. CRASH DAMAGE Because of the many possible combinations that can result from crash damage, it is not possible to include the specific repair tasks in this category. The helicopter mechanic must make an analysis of the crash damage for each situation. Do the repair in accordance with the degree of damage to the specific part and the applicable repair procedures in this manual. Call Bell Helicopter Textron Product Support Engineering with your analysis of the crash damage. 5-4. TYPES OF INSPECTIONS 1. The maintenance procedures may include scheduled inspections, special inspections, conditional inspections, component interim inspections, and component overhaul inspections. a. Scheduled inspections must occur at specified operating intervals. The intervals may be in operating time (hours), cycles, torque events (RIN), calendar (days, months, years), or other assigned units. This makes sure that the helicopter is airworthy. b. Special inspections are of a temporary nature or of a special interval that is not consistent with the scheduled inspections. c. Conditional inspections do not occur at a specified time. A conditional inspection is the result of known or suspected unusual event, known or suspected malfunctions, or defects. d. An interim inspection occurs between overhauls. e. The component overhaul schedule gives the elapsed operating time at which a component must be removed, disassembled, examined for condition, and overhauled, in accordance with data approved by Bell Helicopter Textron. 2. Lubrication and servicing requirements are in addition to those stated in this chapter (Chapter 12). 3. For corrosion control refer to the Corrosion Control Guide, CSSD-PSE-87-001 and the BHT-ALL-SPM. 4. For the CT7-2A engine, refer to the manufacturer’s Maintenance Manual for the scheduled inspection, special inspection, conditional inspection, and component overhaul schedule. 5. For the common Bell Helicopter Textron approved optional equipment that is integrated into this Maintenance Manual, refer to this chapter for the scheduled inspection, conditional inspection, component interim inspection, and component overhaul inspection. 6. For all other Bell Helicopter Textron approved equipment, refer to the applicable Service Instruction (SI) for the scheduled inspection, special inspection, BHT-214ST-MM 5-00-00 22 FEB 2013 Rev. 9 Page 5 Export Classification C, ECCN EAR99 conditional inspection, component interim inspection, and component overhaul inspection. 7. For the inspection requirements for optional equipment approved under Supplement Type Approval/Certificate (STA/STC), refer to the applicable STA/STC documentation. Maintenance and inspection of these items are the responsibility of the owner/ operator. 5-5. DEFINITIONS • Examine — Look carefully to find the condition of the component. Find how that condition relates to a specific standard. • Condition — The state of an item compared to a known standard. • Security — The presence of attaching parts that are properly tightened or appear to be, and the presence of properly installed (as required) locking devices such as lockwire, cotter pins, or other. • Standard — A specified rule or measure that you use to find the condition of a component. • Damage — Physical deterioration of a component. • Discard — Reject a component that has damage that cannot be repaired. To permanently remove from service. • Inspection — A procedure that includes checking, inspecting, and examining a system or a component. • Non scheduled inspection — An inspection that has not been scheduled. • Periodic inspection — An inspection that is repeated at equal time intervals. • Maintenance — The servicing and/or the repair of a helicopter, a system, or a component that keeps it serviceable. • Preventive maintenance — To do small maintenance action(s) on a regular basis to prevent non scheduled maintenance. • Operating time — Actual flight or calendar time that must be recorded in the Historical Service Records or in the helicopter logs. The operating time is specified as: – Time in service (flight time) — The measured time that starts the moment the helicopter leaves the ground and continues until it touches the ground at the next point of landing. The time when the helicopter is on the ground, with the engine and the rotor turning, is not included. – Calendar time — The elapsed time starts on the day the inspection is completed, the component is installed, or the rotor is turned for the first time and ends on the last day of the month that the time limit expires. Calendar time is continuous. Calendar time does not stop when you remove a component, put the helicopter in storage, etc. • Lead-the-Fleet (LTF) program — This is a program to validate the performance of an approved 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 through a plan and the engineering and maintenance aspects will be approved by the regulatory authorities. BHT-214ST-MM 5-00-00 Page 6 Rev. 9 22 FEB 2013 Export Classification C, ECCN EAR99 5-6. INSPECTION AND OVERHAUL TOLERANCE WARNING DO NOT APPLY THESE TOLERANCES T O P A R T S W I T H A L I M I T E D AIRWORTHINESS LIFE (CHAPTER 4). The Bell Helicopter Textron approved tolerance for scheduled inspections, special inspections, interim inspections, and overhaul intervals, unless otherwise stated, is 10% or up to a maximum of 100 hours operating time/30 days calendar time, whichever is less. The tolerances are established for maintenance scheduling convenience only. Scheduled inspections, special inspections, interim inspections, or overhaul intervals required beyond the stated tolerances must be approved by Product Support Engineering. NOTE The following is only applicable for those operators whose governing aviation authority requires to specifically approve the inspection and overhaul tolerance. If approval of the inspection and overhaul tolerance is required by the applicable governing aviation authority, this is the responsibility of the owner/operator. Refer to the CT7-2A Maintenance Manual for inspection and overhaul tolerances. 5-7. MAINTENANCE ZONES Figure 5-1 and Figure 5-2 provide the location of various maintenance and structural significant items to facilitate maintenance planning for the 214ST helicopter for owners or operators who desire to develop a progressive inspection system. These locations are depicted as zones. 1. Major zones. Major zones are designated by a three digit number (100, 200, etc.). 2. Sub-major zones. These zones are subdivisions of major zones (110, 120, etc.). Zones that are a subdivision of sub-major zones are designated (111, 112, 113, etc.). BHT-214ST-MM 5-00-00 22 FEB 2013 Rev. 9 Page 7 Export Classification C, ECCN EAR99 Figure 5-1. Major Zones BHT-214ST-MM 5-00-00 Page 8 Rev. 9 22 FEB 2013 Export Classification C, ECCN EAR99 Figure 5-2. Sub-major Zones (Sheet 1 of 4) BHT-214ST-MM 5-00-00 22 FEB 2013 Rev. 9 Page 9 Export Classification C, ECCN EAR99 Figure 5-2. Sub-major Zones (Sheet 2 of 4) BHT-214ST-MM 5-00-00 Page 10 Rev. 9 22 FEB 2013 Export Classification C, ECCN EAR99 Figure 5-2. Sub-major Zones (Sheet 3 of 4) BHT-214ST-MM 5-00-00 Export Classification C, ECCN EAR99 Figure 5-2. Sub-major Zones (Sheet 4 of 4) 22 FEB 2013 Rev. 9 Page 11/12 BHT-214ST-MM 5-00-00 Export Classification C, ECCN EAR99 SCHEDULED INSPECTION 5-8. SCHEDULED INSPECTIONS WARNING FAILURE TO CORRECT CONDITIONS S U C H A S , B U T N O T L I M I T E D T O , CORROSION, EROSION, MECHANICAL DAMAGE, OR OBVIOUS WEAR FOUND DURING A SCHEDULED INSPECTION C O U L D S E R I O U S L Y A F F E C T T H E AIRWORTHINESS OF THE HELICOPTER. Scheduled inspections include the airframe and the component inspections. The scheduled airframe inspection intervals are related to the airframe operating time. The scheduled component inspection intervals are related to the component operating time. Inspect the helicopter each 25 hours/7 days, 250 hours, 500 hours, 1000 hours/1 year, and 5000 hours/5 years of operation to ensure airworthiness. 22 FEB 2013 Rev. 9 Page 13/14 BHT-214ST-MM 5-00-00 22 FEB 2013 Rev. 9 Page 15 Export Classification C, ECCN EAR99 SCHEDULED INSPECTIONS 5-9. A — INSPECTION (25 HOURS/7 DAYS) DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER DATE: __________________W.O. _____________________ FACILITY: __________________________________________ HELICOPTER S/N: ___________________________________ REGISTRY NO.: _____________________________________ TOTAL TIME:_______________________________________ SIGNATURE:________________________________________ NOTE The A-Inspection consists of visual checks and inspection of special items, and is repeated every 25 flight hours or 7 calendar days, whichever occurs first. It is a maintenance inspection performed by qualified maintenance personnel. The A-Inspection may be preceded by other checks such as preflight or in-transit checks depending on the individual Air Transport and Commercial Operators (ATCO) operation. Portions of the A-Inspection may be delegated to one or more of these lesser checks. GENERAL 1. Each listed inspected item or maintenance function is to be performed in accordance with the referenced Maintenance Manual or the BHT-214ST-CR&O Manual chapter specified. 2. Refer to the engine manufacturer’s Maintenance Manual for engine inspection requirements. PRELIMINARY REQUIREMENTS Chapter 4 1. Replace all finite life components that have completed published operating limitations. Chapter 5 2. Overhaul all components that have completed published overhaul periods. BHT-214ST-MM 5-00-00 Page 16 Rev. 9 22 FEB 2013 Export Classification C, ECCN EAR99 Chapter 12 3. Lubricate and service helicopter as required. Chapter 5 4. Review Special Inspections and perform special inspections as required. Service Instruction (SI) 5. Comply with all inspections and test requirements of all installed kits. FORWARD FUSELAGE NOTE The following items shall be inspected for general condition and as otherwise noted. General condition includes obvious damage, deformation, security of attachment, and evidence of fluid leakage. Chapter 26 1. Pilot portable fire extinguisher for proper servicing. 2. Passenger portable fire extinguisher for proper servicing. Chapter 52 3. Crew doors jettison system. 4. Inspect life raft painter line installation for retainer damage, security, loose or missing fasteners. Chapter 25 5. Visually inspect cargo hook and suspension assembly for condition, security, electrical connections, and cable entries for proper sealing. 6. Bottom skin for evidence of fuel tank leaks. Chapter 29 7. Utility hydraulic module filter(s) bypass indicator not extended. If extended, proceed as follows: a. Pre TB 214ST-89-98, clean utility hydraulic system module assembly filter element 205-076-034-007. If filter element 205-076-034-101 is installed, it must be replaced. b. Post TB 214ST-89-98 and 214ST S/N 28185 and subsequent, replace affected filter element. Chapter 67 8. Tail rotor hydraulic actuator. SCHEDULED INSPECTIONS 5-9. A — INSPECTION (25 HOURS/7 DAYS) (CONT) DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER 1 BHT-214ST-MM 5-00-00 22 FEB 2013 Rev. 9 Page 17 Export Classification C, ECCN EAR99 Chapter 63 9. Nodal beam assembly. 10. Aft pylon support clevis assemblies for cracks. Chapter 32 LANDING GEAR 1. Cross tubes for security and excessive deflection. 2. Skid tubes. 3. Main landing gear, wheels, tires, and brake assemblies. 4. Main landing gear strut for proper inflation. 5. Nose landing gear shimmy damper. 6. Nose landing gear strut for proper inflation. 7. Nose landing gear, wheel, and tire. 8. Emergency float switches for condition and security of attachment. PYLON Chapter 29 1. PC1 and PC2 hydraulic mode filter bypass indicators not extended. If extended, clean affected filter element. Chapter 63 2. Main rotor gearbox assembly. Chapter 62 3. Main rotor mast. Chapter 63 4. Rotor brake disc; brake linings for excessive wear indications. 5. Main drive shaft; inspect main driveshaft couplings for evidence of grease leakage, visually inspect driveshaft for corrosion and surface damage. Perform serviceability check of over-temperature TEMP-PLATES. 6. Combining gearbox assembly. SCHEDULED INSPECTIONS 5-9. A — INSPECTION (25 HOURS/7 DAYS) (CONT) DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER 2 2 3 3 3 3 3 BHT-214ST-MM 5-00-00 Page 18 Rev. 9 22 FEB 2013 Export Classification C, ECCN EAR99 7. Inspect for clearance and proper clamping between generator power cables and hydraulic lines at the forward end of the combining gearbox. Chapter 71 8. Bipod and tripod forward engine mount assemblies. Chapter 67 9. Main rotor hydraulic actuators; control tube rod ends for evidence of loose bearings. Actuator linkage stop lock for damage and the linkage stop is aligned and centered between flanges of input lever. Chapter 65 10. Tail rotor drive coupling; inspect tail rotor driveshaft coupling at transmission tail rotor drive quill for grease leakage, corrosion, and surface damage. Perform serviceability check of over-temperature TEMP-PLATES. Chapter 25 11. Check life raft cowl manual opening mechanism for ease of operation. Check mechanism for corrosion. Check latches for engagement and security. Chapter 62 12. Pitch links. 13. Scissors and sleeve assembly. 14. Swashplate and support assembly. 15. Swashplate ring assembly lubrication. 16. Collet clamp. NOTE Lower hub nut slippage inspection not required for hub assembly 214-010-505-109 when used with nut 214-010-417-103. C-Inspection (500 hours) is still required. 17. Scissors and sleeve collective hub lower nut for evidence of movement. If nut movement or loss of torque is evident, remove and disassemble scissors and sleeve. SCHEDULED INSPECTIONS 5-9. A — INSPECTION (25 HOURS/7 DAYS) (CONT) DATA REFERENCE INSPECTION TASK DESCRIPTION INITIAL MECH OTHER