AW139 - AMP! CHAPTER 4 ISSUE 9

and is supplied on the express condition that it may not be disclosed to any third party, or reproduced in whole or in part, or used for manufacture, or used for any purpose other than for which it is supplied, without the prior written consent of the Companies. Every permitted disclosure, reproduction, adaptation or publication of this document in whole or in part and in any manner or form shall prominently contain this notice.. 1 SCOPE This report is issued to include the MAF (Manual Approval Form) information as referred in [1]. 2 REFERENCES [1] C750-02-003.1 – DOA Handbook [2] AWEOP002 – Signature Procedure For Technical Documentation [3] 100-50-175 Compliance Verification Engineers (CVE) and Airworthiness Engineer (AE): Tasks Responsibilities, Operating Procedures 3 MANUAL APPROVAL FORM The information pertinent to the MAF are reported in Annex A of this document. This report is issued in conformity with Ref. [2] with the clarification that both Area Approval and Authorization signatures have been undertaken by Authorization (CPE) approval. The signatures for the technical content of the document AMPI CHAPTER 4 ISSUE 9 (reported in Annex A) for the responsibilities defined in [3] according to [1] are those reported on the first page of this document. 4 COMPLIANCE ASSESSMENT The scope of this report is to provide compliance with the JAR 29 Amdt.3 requirement listed below: JAR 29.1529 — Instructions for Continued Airworthiness”. Appendix A — Instruction for Continued Airworthiness (Paragraph A29.1, A29.2 and A29.4 AW139 – AMPI CHAPTER 4 ISSUE 9 139G0255A045 Rev. A Pag. 6 of 7 © Copyright Leonardo S.p.a. Helicopters, AgustaWestland Limited, AgustaWestland Philadelphia Corporation 2016 This document contains information that is confidential and proprietary to Leonardo S.p.a. Helicopters and/or AgustaWestland Limited and/or AgustaWestland Philadelphia Corporation (‘the Companies’) and is supplied on the express condition that it may not be disclosed to any third party, or reproduced in whole or in part, or used for manufacture, or used for any purpose other than for which it is supplied, without the prior written consent of the Companies. Every permitted disclosure, reproduction, adaptation or publication of this document in whole or in part and in any manner or form shall prominently contain this notice.. 5 CERTIFICATION PROGRAM AND APPLICABILITY This report is in accordance with the certification program as indicated in the following NDC:
NDC 139G6220-008 - M/R DAMPER - IMPROVEMENT OF THE INSPECTION PROGRAM
NDC 139G0255-035 - AMPI CHAPTER 4 - ISSUE 9 Note: the responsibility of the CVEs for the signature of this document is reported in the applicable CCLs. 6 CHANGE DESCRIPTION The following change will be introduced in Chapter 4 issue 9: Retirement lives
The retirement life of the M/R damper Body End Assy P/N M006-01H046-041 every 2400 FH. In addition to this, a note will be added to specify that the M/R damper P/N 3G6220V001353 must be sent to the manufacturer when the M/R damper Body End Assy P/N M006-01H046-041 reaches 2400 FH. Note that according to the results of the Compliance Statement 139G6220-008/02, a fatigue life of 39,000 FH has been demonstrated for the M/R damper P/N 3G6220V001353. LHD, on voluntary basis, decided to report in the AMPI Chapter 4 a retirement life of 2400 FH to align the Life of the damper with the Overhaul currently published in AMPI Chapter 5.
The retirement life of the M/R blade P/N 3G6410A00131 will be extended from 16,800 FH or 50,200 landings to 20,000 FH or 50,200 Landings retaining the Rotor Starting or Stopping with wind speed above 33 kts - Life penalty factor;
The retirement life of the M/R blade P/N 3G6410A00134 will be deleted;
The retirement life of the TR Hub P/N 3G6420A00332 will be extended from 11,250 FH or 67,500 landings to 34,500 FH or 207,000 landings;
The retirement life of the MGB Upper Fitting P/N 3G6330A00232 will be extended from 95,600 Landings to 133,240 Landings and the penalty factors for operation above 6400 Kg has been removed;
Table 7 “Operation above 6400 Kg (MTOW) – Life penalty factor” will be modified to remove the RL024 “MGB upper Fitting” and to add RL021A (typo) “MGB case, Top Assembly (with Circular Force Active Vibration Control System installed). AW139 – AMPI CHAPTER 4 ISSUE 9 139G0255A045 Rev. A Pag. 7 of 7 © Copyright Leonardo S.p.a. Helicopters, AgustaWestland Limited, AgustaWestland Philadelphia Corporation 2016 This document contains information that is confidential and proprietary to Leonardo S.p.a. Helicopters and/or AgustaWestland Limited and/or AgustaWestland Philadelphia Corporation (‘the Companies’) and is supplied on the express condition that it may not be disclosed to any third party, or reproduced in whole or in part, or used for manufacture, or used for any purpose other than for which it is supplied, without the prior written consent of the Companies. Every permitted disclosure, reproduction, adaptation or publication of this document in whole or in part and in any manner or form shall prominently contain this notice.. Mandatory Inspections
The Note 2 applicable to the inspections MI62-01 and MI64-01 will be changed to modify the wind speed value from 27 Kts to 33 Kts;
The Note 7 will be changed to correct a typo. In particular the P/N 3G5306P22311 will be replaced by the P/N 3G5306P08513. AW139 – AMPI CHAPTER 4 ISSUE 9 139G0255A045 Rev. A Pag. A1 of A27 © Copyright Leonardo S.p.a. Helicopters, AgustaWestland Limited, AgustaWestland Philadelphia Corporation 2016 This document contains information that is confidential and proprietary to Leonardo S.p.a. Helicopters and/or AgustaWestland Limited and/or AgustaWestland Philadelphia Corporation (‘the Companies’) and is supplied on the express condition that it may not be disclosed to any third party, or reproduced in whole or in part, or used for manufacture, or used for any purpose other than for which it is supplied, without the prior written consent of the Companies. Every permitted disclosure, reproduction, adaptation or publication of this document in whole or in part and in any manner or form shall prominently contain this notice.. ANNEX A TITLE Manual Approval Form 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 1 16 Retirement lives General Table of contents Page 1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 2 Retirement lives - Affected parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 3 Terms and definitions of Table 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 3.1 Reference (Ref) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 3.2 Part. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3.3 Part number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3.4 Retirement life . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 4 External Hoist Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 5 External Load Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 6 Operation above 6400 kg (MTOW) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 7 Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 List of tables Page Table 1 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Table 2 Retirement lives - List of affected parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 Table 3 CAT. A Training Operations - Life penalty factor . . . . . . . . . . . . . . . . . . . . . . . . . 9 Table 4 Rotor Starting or Stopping with wind speed above 33 kts - Life penalty factor. . . 10 Table 5 External Hoist Lift - Life penalty factor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 Table 6 External Load Operation - Life penalty factor. . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 Table 7 Operation above 6400 kg (MTOW) - Life penalty factor. . . . . . . . . . . . . . . . . . . . 13 List of figures Page 1 Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 References Description 1 Introduction The parts listed in the Table 2 - Retirement lives - List of affected parts must be mandatorily retired from service when the indicated retirement life is reached. This also applies to all those non-serialized standard parts which connect the identified assembly / component. Table 1 References Data module/Technical publication Title No references 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 2 All retirement lives are expressed in Flying Hours (FH), unless otherwise specified. Flying hours are defined as those hours accumulated from take-off to landing. The retirement lives of some parts are expressed in “landings” because their life is dependent upon the rotor start-stop cycles and the helicopter ground-air-ground cycles. Note If the number of landings applicable to the component is not known throughout the entire service life of the component, the number of landings shall be calculated multiplying the component flight hours by a factor of 6. If not differently specified, the retirement lives are based on the following assumptions: – 800 landings in 100 flying hours, including 400 rotor start-stop cycles. – 20 percent of usage in CAT. A Training Operations, on yearly basis. – For External Load Operations: 6 External Load Cycles and 3 Landings per Flying Hour, cal- culated on at least 100 FH basis – For External Hoist Operations: 1.65 Lift per Flying Hour, calculated on at least 100 FH basis. In the event that the actual usage exceeds these assumptions, the Operator shall contact the Manufacturer. If parts with the same part number have been interchanged between different AW139 variants and different AW Helicopter models, the retirement life of the part must be restricted to the lowest value between those variants/models on which the part has been installed. Note 1 For the following parts the Operator shall maintain the relevant log card and contact the Manufacturer prior to approaching the 40000 FH for confirmation of the applicability of the airworthiness instructions provided in this chapter: – Fuselage Assembly, P/N 3G5300X00132 – Fuselage Structure Assembly, P/N 3P5300A00131 – Tail Assembly, P/N 3G5350A00135 plus retromod P/N 3G5309P02711 – Tail Assembly, P/N 3G5350A00136. Note 2 For the following Tail Fin Assemblies the life limit is aligned with the life limit applicable to the corresponding Tail Assembly (refer to the related Log Card): – Tail Fin Assembly, P/N 3G5351A00133 part of the Tail Assembly P/N 3G5350A00132 – Tail Fin Assembly, P/N 3G5351A00134 part of the Tail Assembly P/N 3G5350A00133 or 3G5350A00134 – Tail Fin Assembly, P/N 3G5351A00135 part of the Tail Assembly P/N 3G5350A00135 – Tail Fin Assembly, P/N 3G5351A00136 part of the Tail Assembly P/N 3G5350A00136. 2 Retirement lives - Affected parts Refer to Table 2 - Retirement lives - List of affected parts. 3 Terms and definitions of Table 2 3.1 Reference (Ref) This column gives a reference [RL (Retirement Lives) plus a progressive number] which identi- fies the listed components. 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 3 16 3.2 Part This column gives the part description. 3.3 Part number This column gives the part number. 3.4 Retirement life This column gives the retirement life of the part. Unless specified differently, the retirement life it in flight hours. Table 2 Retirement lives - List of affected parts Ref Part Part number Retirement life RL001 Left Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00133 21000 landings Left Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00135 50000 landings Deleted Right Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00233 21000 landings Right Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00235 50000 landings Deleted RL001A Left Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00831 25000 landings RL001C Left Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00832 50000 landings RL001B Right Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00931 25000 landings RL001D Right Main Landing Gear Assembly (Liebherr landing gear installation) 3G3210V00932 50000 landings RL002 Nose Landing Gear Assembly (Liebherr landing gear installation) 3G3220V00133 50000 landings Deleted RL002A Nose Landing Gear Assembly (Goodrich landing gear installation) 4G3220V00131 50000 landings RL003 Main Retracting Actuator Assembly (Liebherr landing gear installation) 3G3230V00332 50000 landings RL003A Main Retracting Actuator Assembly (Goodrich landing gear installation) 4G3230V00233 50000 landings RL004 Nose Retracting Actuator Assembly (Liebherr landing gear installation) 3G3230V00132 50000 landings 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 4 RL004A Nose Retracting Actuator Assembly (Goodrich landing gear installation) 4G3230V00131 50000 landings RL004B Left MLG Trailing Arm Assembly (Goodrich landing gear installation) 4G3210V00331 50000 landings RL004C Right MLG Trailing Arm Assembly (Goodrich landing gear installation) 4G3210V00431 50000 landings RL004D MLG Shock Absorber Assembly (Goodrich landing gear installation) 4G3210V00531 50000 landings RL004E Forward Arm Assembly (Goodrich landing gear installation) 4F3210A00131 50000 landings RL005 TGB Fitting 3G5351A01151 7200 RL006 Tail Assembly 3G5350A00132 19600 FH or 32000 landings whichever comes first (Para 5 ) (Note 8) (Note 12) RL006A Tail Assembly 3G5350A00136 See Note 1 Para 1 RL006B Tail Assembly 3G5350A00135 32000 landings (Note 9) RL007 Main Landing Gear LH Segment 3P5339A00332 80000 landings Main Landing Gear RH Segment 3P5339A00432 80000 landings RL007A Rear Fuselage Assembly 3P5340A00132 32000 landings (Note 10) (Note 11) RL007B Trailing Arm Pintle Pin (Goodrich landing gear installation) 3G5339A08351 37500 landings RL008 Tailplane Attachment Fitting on Fin Upper 3G5351A01432 7600 Tailplane Attachment Fitting on Fin Upper 3G5351A01532 7600 RL009 Tailplane Attachment Fitting on Fin Lower 3G5351A07531 10600 RL009A Tailplane upper LH fitting 3G5309P03031 7600 RL009B Tailplane upper LH fitting 3G5351A08931 7600 RL009C Tailplane upper RH fitting 3G5309P03131 7600 RL009D Tailplane upper RH fitting 3G5351A09031 7600 RL009E Tailplane lower fitting 3G5351A09131 10600 RL010 Deleted RL010A Rod End (Fin End) 3G5510A03931 4600 (Para 6 ) RL010B Rod Sleeve 3G5510A04152 10000 Table 2 Retirement lives - List of affected parts Ref Part Part number Retirement life 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 5 16 RL010C Rod End (Tailplane End) 3G5510A04052 10000 (Para 6 ) RL010D Tailplane Assembly 3G5510A00133 65000 (Para 6 ) RL010E Rod assembly (Tailplane) 3G5510A08931 4600 (Para 6 ) RL011 Main Landing Gear Actuator Bolt on Sponson Bracket 3G3210L00151 160000 landings RL012 Main Rotor Blade Assembly 3G6210A00131 20000 FH or 50200 landings whichever comes first (Table 4) (Note 4) RL012A Main Rotor Blade Assembly with Heater Mat 4G6210A00132 10000 FH or 50200 landings whichever comes first (Table 4) (Note 5) RL012B Deleted RL013 Main Rotor Hub Assembly 3G6220A00332 46000 (Para 5 ) RL014 Deleted RL015 Main Rotor Rotating Swashplate 3G6230A00332 4800 (Para 4 ) RL015A Main Rotor Rotating Swashplate Assy reworked 3G6206P01331 4800 (Para 4 ) RL015B Main Rotor Rotating Swashplate 3G6230A00333 17300 (Para 4 ) RL015C Locking Ring Outer 3G6230A03153 7700 RL016 Main Rotor Scissors Attachment Flange Assembly 3G6220A00632 47450 RL016A Main Rotor Scissors Attachment Flange Assembly 3G6220A00633 Unlimited RL017 Main Rotor Damper Bolt 3G6220A01251 51700 RL018 Main Rotor Elastomeric Bearing 3G6220V00153 100000 landings Main Rotor Elastomeric Bearing 3G6220V00154 100000 landings RL019 Upper Scissor Lever Assembly 3G6230A00832 14300 RL019A Deleted RL019B Lower Scissor Lever Assembly 3G6230A00931 20100 RL019C Upper Scissor Lever Assembly 3G6230A00834 Unlimited RL019D Lower Scissor Lever Assembly 3G6230A00934 Unlimited RL020 Deleted RL021 MGB Case, Top Assembly (without Circular Force Active Vibration Control System installed) 3G6320A01033 8800 FH or 23000 landings whichever comes first (Para 6 ) (Note 7) MGB Case, Top Assembly 3G6320A01035 120000 landings Table 2 Retirement lives - List of affected parts Ref Part Part number Retirement life 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 6 RL021A MGB case, Top Assembly (with Circular Force Active Vibration Control System installed) 3G6320A01033 7600 FH or 20000 landings whichever comes first (Para 6 ) (Note 7) RL021B MGB case, Top Assembly 3G6320A16231 120000 landings RL022 MGB Shaft, Main Rotor 3G6320A01852 15300 FH or 54000 landings whichever comes first (Table 3) and (Para 4 ) and (Para 5 ) RL023 MGB Case, Main Assembly 3G6320A02734 5000 FH or 27000 landings whichever comes first (Para 5 ) MGB Case, Main Assembly 3G6320A02736 12500 FH or 61800 landings whichever comes first (Para 5 ) RL023A MGB Case, Main Assembly 3G6320A16331 12500 FH or 61800 landings whichever comes first (Para 5) RL024 MGB Upper Fitting 3G6330A00232 133240 landings RL025 MGB Antitorque Beam 3G6330A00532 20000 FH or 63000 landings whichever comes first (Para 5 ) RL026 Deleted RL027 Deleted RL028 Deleted RL029 Deleted RL030 Deleted RL031 Deleted RL032 Deleted RL033 Tail Rotor Blade Assembly 3G6410A00131 10000 RL033C Tail Rotor Blade Assembly 3G6410A00132 1200 FH or 3200 landings wichever comes first RL033D Tail Rotor Blade Assembly 3G6410A00133 40000 landings RL033A Tail Rotor Blade Assembly with Heater Mat 4G6410A00131 4033 RL033E Tail Rotor Blade Assembly with Heater Mat 4G6410A00132 1200 FH or 3200 landings wichever comes first RL033F Tail Rotor Blade Assembly with Heater Mat 4G6410A00133 4033 FH or 40000 landings wichever comes first RL033G Tail Rotor Blade Damper bracket 3G6410A03631 27600 RL033B Tail Rotor Blade Bolt 3G6420A00252 19100 (Note 2) Table 2 Retirement lives - List of affected parts Ref Part Part number Retirement life 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 7 16 RL034 Tail Rotor Hub Assembly 3G6420A00332 34500 FH or 207000 landings whichever comes first RL035 Tail Rotor Elastomeric Spherical Bearing 3G6420V00153 5000 Tail Rotor Elastomeric Spherical Bearing 3G6420V00154 5000 RL036 Tail Rotor Elastomeric Damper 3G6420V00455 20000 RL036A Tail Rotor Elastomeric Damper 3G6420V00851 12600 RL037 Tail Rotor Shaft Drive Assembly, Number 1 3T6510A00141 100000 landings (Para 5 ) Tail Rotor Shaft Drive Assembly, Number 2 3T6510A00238 16000 FH or 44800 landings whichever comes first (Para 5 ) (Para 6 ) Tail Rotor Shaft Drive Assembly, Number 3 3T6510A00337 16000 FH or 44800 landings whichever comes first (Para 5 ) (Para 6 ) RL038 Tail Rotor Drive Coupling 3T6510V00152 60000 landings (Para 5 ) RL039 Deleted RL040 TGB Input Flange Coupling 3T6521A07353 100000 landings (Para 5 ) RL041 IGB Output Flange Coupling 3T6521A07353 100000 landings (Para 5 ) RL042 TGB Output Housing 3T6522A05338 48000 landings (Para 5 ) RL042A TGB Output Housing 3T6522A05341 100000 landings (Para 5 ) RL043 TGB Centre Housing 3T6522A05144 10000 FH or 72200 landings whichever comes first RL043A TGB Centre Housing 3T6522A05147 23000 FH or 94200 landings whichever comes first (Para 5 ) RL044 IGB Input Flange Coupling 3G6521A00231 100000 landings (Para 5 ) IGB Input Flange Coupling 3T6521A05657 100000 landings (Para 5 ) RL045 IGB Housing assy centre 3T6521A05134 100000 landings (Para 5 ) RL046 Deleted Table 2 Retirement lives - List of affected parts Ref Part Part number Retirement life 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 8 RL047 External (Rescue) Hoist Cable Assembly BL-6260 1500 external hoist lifts or 4 years, whichever occurs first (see Para 4 for External Hoist Lift definitions) External (Rescue) Hoist Cable Assembly BL-9149-8 1500 external hoist lifts or 4 years, whichever occurs first (see Para 4 for External Hoist Lift definitions) External (Rescue) Hoist Cable Assembly 42325-298 1500 external hoist lifts or 4 years, whichever occurs first (see Para 4 for External Hoist Lift definitions) RL048 Antitorque Beam Bolts 3G6330V00451 3G6330L00351 56000 RL049 Deleted RL050 Deleted RL051 Deleted RL052 Tail Rotor Servoactuator 3G6730V00731 44000 (Note 6) (Para 5 ) RL053 Main rotor damper body end assembly M006-01H046-041 2400 (Note 13) Notes 1 The specified limit is intended since first opening of the sealed bag. 2 Record the effective accumulated life of the Tail Rotor Blade Bolt P/N 3G6420A00252 on applicable Log Card at receiving date of Chapter 4 Issue 3. Otherwise, if the effective accumulated life is unknown record a forfait accumulated life of 9000 FH. This is applicable to all bolts including those in stock. 3 Deleted. 4 If the number of landings is not known throughout the entire service life of the Main Rotor Blade Assembly P/N 3G6210A00131, the number of landings shall be calculated multiplying the blade flight hours by a factor of 4. 5 If the number of landings is not known throughout the entire service life of the Main Rotor Blade Assembly P/N 4G6210A00132, refer to the note reported at Para 1 of AMPI CHAPTER 04 AIRWORTHINESS LIMITATIONS - Retirement lives- General (39-A-04-10-00-00A-028E-P). 6 Record the effective accumulated life of the Tail Rotor Actuator P/N 3G6730V00731 on applicable Log Card at receiving date of Chapter 4 Issue 3 Change 5. Otherwise, if the effective accumulated life is unknown record a forfait accumulated life of 11000 FH. This is applicable to all Tail Rotor Actuator including those in stock. 7 If the part is once installed on an AW139 helicopter equipped with the Circular Force Active Vibration Control System, the applicable life limit is restricted permanently to 7600 FH or 20000 landings. Table 2 Retirement lives - List of affected parts Ref Part Part number Retirement life 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 9 16 8 When retromod P/N 3G5309P02711 and P/N 3G5309P01812 are applied to the Tail Assembly P/N 3G5350A00132, 3G5350A00133 or 3G5350A00134, the retirement life is extended to 19600 FH or 78600 landings, whichever comes first. The External Load Operation penalty factor is retained. 9 When retromod 3G5309P02711 is applied to the Tail Assembly P/N 3G5350A00135, the life limit is not applicable but the Operator shall maintain the relevant log card and contact the Manufacturer prior to approaching the 40000 FH for confirmation of the applicability of the airworthiness instructions provided in this chapter. 10 When retromod 3G5306P38811 is applied to Rear Fuselage 3P5340A00132 or 3P5340A00133, the life limit of 32000 landings is superseded. The Operator shall maintain the relevant log card and contact the Manufacturer prior to approaching the 40000 FH for confirmation of the applicability of the airworthiness instructions provided in this chapter. 11 If Rear Fuselage 3P5340A00134 or 3G5340A11131 is installed, the life limit of 32000 landings is superseded. The Operator shall maintain the relevant log card and contact the Manufacturer prior to approaching the 40000 FH for confirmation of the applicability of the airworthiness instructions provided in this chapter. 12 When retromod P/N 3G5309P01511 is applied before having accumulated 12500 FH or 50000 landings, whichever comes first, to the Tail Assembly P/N 3G5350A00132, 3G5350A00133 or 3G5350A00134, equipped with retromod P/N 3G5309P02711 and 3G5309P01812, the retirement life is extended to 33700 FH. The External Load Operation penalty factor is retained 13 For main rotor damper body end assembly replacement, send P/N 3G6220V01353 to the Manufacturer. Table 3 CAT. A Training Operations - Life penalty factor Ref Part Part number Life penalty factor RL012 Deleted RL012A Deleted RL012B Deleted RL022 MGB Shaft, Main Rotor 3G6320A01852 1.7 RL031 Deleted Note CAT. A Training Operations – For the parts listed in Table 3 - CAT. A Training Operations - Life penalty factor a life penalty must be mandatorily applied whenever CAT. A Training Operations are performed. – Flying hours (FH) spent in CAT. A Training must be multiplied by the specified factor. The penalty is applicable only to flying hours. – FH spent in CAT. A Training Operations are defined as the total flying Hours (from take off to landing) when at least one time the training mode is activated. – E.g.: MGB Shaft, Main Rotor: Flight time spent during CAT. A Training Opera- tions = 1 FH. Total accumulated FH = 1 x 1.7 = 1.7 FH. Table 2 Retirement lives - List of affected parts Ref Part Part number Retirement life 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 10 Table 4 Rotor Starting or Stopping with wind speed above 33 kts - Life penalty factor Ref Part Part number Life penalty factor 33 kts<wind speed<45 kts Life penalty factor 45 kts<wind speed<60 kts RL012 Main Rotor Blade Assembly 3G6210A00131 3 landings 14 landings RL012A Main Rotor Blade Assem- bly with Heater Mat 4G6210A00132 3 landings 14 landings RL012B Deleted Note Rotor Starting or Stopping with wind speed above 33 kts – For the parts listed in Table 4 - Rotor Starting or Stopping with wind speed above 33 kts - Life penalty factor a life penalty must be mandatorily applied. – Increase the landings by the specified value for each Rotor Start or Stop carried out with wind speed above 33 kts. – E.g.: Main Rotor Blade Assembly part number 3G6210A00131: Rotor Start with 33 kts<wind speed<45 kts. Flight Time = 1 FH. Rotor Stop with 33 kts<wind speed<45 kts. Landings = 1 Total accumulated FH = 1 FH. Total consumed landings = 3 + 1 + 3 = 7 landings. – E.g.: Main Rotor Blade Assembly part number 3G6210A00134: Rotor Start with 45 kts<wind speed<60 kts. Flight Time = 1 FH. Rotor Stop with 45 kts<wind speed<60 kts. Landings = 1. Total accumulated FH = 1 FH. Total consumed landings = 14 + 1 + 14 = 29 landings. – E.g.: Main Rotor Blade Assembly part number 4G6210A00132: Rotor Start with 33 kts<wind speed<45 kts. Flight Time = 1 FH. Rotor Stop with 45 kts<wind speed<60 kts. Landings = 2. Total accumulated time FH = 1 FH. Total consumed landings = 3 + 2 + 14 = 19 landings. 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 11 16 4 External Hoist Operation For the parts listed in Table 5 - External Hoist Lift - Life penalty factor a life penalty must be man- datorily applied whenever an external hoist lift is performed. The external hoist lift is defined as an unreeling and recovery of the cable with a load attached to the hook, independent of the length of the cable that is deployed/recovered. An unreeling/recov- ery of the cable with no load on the hook is not considered to be a lift. Any operation where a load is applied for half the operation (i.e. unreeling or recovery) must be considered as one lift. Increase the flying hour by the specified value for each external hoist lift. The penalty is applica- ble only to flying hours. Table 5 External Hoist Lift - Life penalty factor Ref Part Part number Life penalty factor RL015 Main Rotor Rotating Swash- plate 3G6230A00332 0.5 (Note 1) RL015A Main Rotor Rotating Swash- plate Assy reworked 3G6206P01331 0.5 (Note 1) RL015B Main Rotor Rotating Swash- plate 3G6230A00333 0.5 FH RL022 MGB Shaft, Main Rotor 3G6320A01852 Note 2 E.g.:Main rotor rotating swashplate: Flight time = 4 FH. Number of rescue hoist lifts = 3. Total accumu- lated FH = 4 + (0.5 x 3) = 5.5. Notes 1 For non zero-time components, whose accumulated life has been counted without this penalty factor, the total accumulated life must be updated as follows: Updated total accumulated flight hours = present total accumulated flight hours + 0.5 x accumulated external hoist lifts. 2 The life penalty factor due to external hoist operations has been deleted. For non zero-time components, whose accumulated life has been counted with the previous penalty factor, the total accumulated life may be updated as follows: Updated total accumulated life = present total accumulated life - 2.5 x accumulated external hoist lifts. Present total accumulated life = 25 FH. Accumulated external hoist lifts = 5. Updated total accumulated life = 25 - 2.5 x 5 = 12.5 FH. 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 12 5 External Load Operation For the following parts in Table 6 - External Load Operation - Life penalty factor a life penalty must be mandatorily applied whenever an External Load Cycle is performed. An External Load Cycle is every external load lift using the Cargo Hook. Increase the Flying Hours and/or Landings by the specified value, as applicable, for each Exter- nal Load Cycle. Table 6 External Load Operation - Life penalty factor Ref Part Part number Life penalty factor RL006 Tail Assembly 3G5350A00132 0.5 FH RL013 Main Rotor Hub Assembly 3G6220A00332 1 FH RL022 MGB Shaft, Main Rotor 3G6320A01852 2 Landings and 1 FH RL023 MGB Case, Main assembly 3G6320A02734 2 Landings MGB Case, Main assembly 3G6320A02736 2 Landings RL023A MGB Case, Main Assembly 3G6320A16331 2 Landings RL025 Antitorque Beam 3G6330A00532 2 Landings and 1 FH RL037 TR Shaft Drive Assembly - 1 3T6510A00141 2 Landings TR Shaft Drive Assembly - 2 3T6510A00238 2 Landings TR Shaft Drive Assembly - 3 3T6510A00337 2 Landings RL038 TR Drive Couplings (KAMATICS) 3T6510V00152 2 Landings RL039 Deleted RL040 TGB Input Flange Coupling 3T6521A07353 2 Landings RL041 IGB Output Flange Coupling 3T6521A07353 2 Landings RL042 TGB Output Housing 3T6522A05338 2 Landings RL042A TGB Output Housing 3T6522A05341 2 Landings RL043A TGB Centre Housing 3T6522A05147 2 Landings RL044 IGB Input Flange Coupling 3G6521A00231 2 Landings IGB Input Flange Coupling 3T6521A05657 2 Landings RL045 IGB Housing assy centre 3T6521A05134 2 Landings RL052 Tail Rotor Servoactuator 3G6730V00731 0.5 FH (Note 1) E.g.: For M/R Hub: Flight time = 2 FH. Number of External Load Cycles = 4. Total accumulated FH = 2 + (1 x 4) = 6 FH. E.g.: For M/R Shaft: Flight time = 5 FH. Number of Lifts = 3. Number of landings = 6. Total accumulated FH = 5 + (1 x 3) = 8 FH. Total accumulated landings = 6 + (2 x 3) = 12 Landings. Note 1 The life penalty must be mandatorily applied to the AW139 Helicopters equipped with the Tail Rotor Elastomeric Damper P/N 3G6420V00851. 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 13 16 6 Operation above 6400 kg (MTOW) For the following parts in Table 7 - Operation above 6400 kg (MTOW) - Life penalty factor a life penalty must be mandatorily applied to every flight (from take off to landing) in case the total weight exceeds 6400 kg at least one time. In this case, Multiply the Flying Hours and/or Landings by the specified value, as applicable. Table 7 Operation above 6400 kg (MTOW) - Life penalty factor Ref Part Part number Life penalty factor RL010A Rod End (Fin End) 3G5510A03931 4.5 FH RL010C Rod End (Tailplane End) 3G5510A04052 4 FH RL010D Tailplane Assembly 3G5510A00133 4 FH RL010E Rod assembly (Tailplane) 3G5510A08931 4.5 FH RL012 Deleted RL012A Deleted RL012B Deleted RL014 Deleted RL021 MGB Case, Top Assembly (without Circular Force Active Vibration Control System installed) (Note 1) 3G6320A01033 1.6 FH RL021A MGB Case, Top Assembly (with Circular Force Active Vibration Control System installed) (Note 1) 3G6320A01033 1.6 FH RL024 Deleted RL034 Deleted RL037 Tail Rotor Shaft Drive Assembly, Number 2 3T6510A00238 2 Landings Tail Rotor Shaft Drive Assembly, Number 3 3T6510A00337 2 Landings E.g.: For ROD END (Fin End): Total daily flight hours = 10 FH. Daily FH related to operations above 6400 Kg = 3 FH. Total Accumulated FH = (10-3) + (4.5 x 3) = 20.5 FH. Note 1 Life penalty factor is not applicable to P/N 3G6320A01035 and subsequents. 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 14 7 Guidelines Daily recording of the following parameters is recommended, refer to Fig 1 : – Flight Hours – Landings (coincides with the number of flights) – Flight Hours performed during Cat. A training as per Note (ref. Table 3 - CAT. A Training Operations - Life penalty factor) – Rotor starts above 33 kts wind speed as per Note (ref. Table 4 - Rotor Starting or Stopping with wind speed above 33 kts - Life penalty factor) – Rotor stops above 33 kts wind speed as per Note (ref Table 4 - Rotor Starting or Stopping with wind speed above 33 kts - Life penalty factor) – External hoist lifts as per Para 4 – External load cycles as per Para 5 – Landings related to operations above 6400 kg as per Para 6 – Flight Hours related to operations above 6400 kg as per Para 6 . 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 15 16 Fig 1 Guidelines ICN-39-A-041000-G-00001-18789-A-001-01 Cat. A operations Ext. Load operations (FH) Consumed Life FH = (7.5 - 0.5) + (1.7 x 0.5) + (1 x 4) = 11.85 FH Ext. Load operations (Landings) Consumed Landings = 6 + (2 x 4) = 14 landings Eg.: 1 - Total Daily Flight Hours = 7.5 FH - Daily Landings (coincides with the number of flight) = 6 - Daily Flight Hours performed during Cat. A training as per Note = 0.5 - Daily external load cycles as per Para 5 = 4 For the main rotor shaft the following applies: Eg.: 2 - Total Daily Flight Hours = 7.5 FH - Daily Landings (coincides with the number of flight) = 6 - Daily Flight Hours performed during Cat. A training as per Note = 0 - Daily rotor starts above 33 kts wind speed as per Note = 2 - Daily rotor stops above 33 kts wind speed as per Note = 1 - Daily external hoist lifts per Para 4 = 0 - Daily external load cycles as per Para 5 = 7 - Daily Landings related to operations above 6400 kg as per Para 6 = 3 - Daily Flight Hours related to operations above 6400 kg as per Para 6 = 2.6 For the antitorque beam the following applies: External operations (Landings) Consumed Landings = 6 + (7 x 2) = 20 landings External Load Cycles (FH) Consumed Life FH = 7.5 + (1 x 7) = 14.5 FH 39-A-AMPI-00-P Applicable to: All 39-A-04-10-00-00A-028E-P 2018-02-15 Page 16 THIS PAGE INTENTIONALLY LEFT BLANK 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 1 10 Mandatory inspections General Table of contents Page 1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 2 Affected parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3 Terms and definitions of Table 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3.1 Reference (Ref) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3.2 Part. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3.3 Task . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3.4 Interval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3.5 Reference (DMC) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 4 External hoist lift . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 List of tables Page Table 1 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Table 2 Mandatory inspections - List of affected parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 Table 3 Mandatory inspections - Rescue hoist system (Breeze) . . . . . . . . . . . . . . . . . . . 8 Table 4 Mandatory inspections - Double rescue hoist system (Goodrich) . . . . . . . . . . . . 8 Table 5 Mandatory inspections - Single rescue hoist system (Goodrich) . . . . . . . . . . . . . 8 Table 6 Rotor Starting or Stopping with wind speed above 33 kts - Additional inspections 8 References Table 1 References Data module/Technical publication Title 39-A-25-91-01-00A-310A-K Rescue hoist - Bumper assembly, cable cutter and cable - General visual inspection 39-A-25-91-01-01A-310A-K Hook assembly (rescue hoist) - General visual inspec- tion 39-A-25-94-01-00A-310A-K Double rescue hoist - Bumper assembly, cable cutter and cable - General visual inspection 39-A-25-96-01-00A-310A-K Single rescue hoist - Bumper assembly, cable cutter and cable - General visual inspection 39-A-53-10-00-00A-310A-A Forward section - Sponsons - General visual inspection 39-A-53-10-00-00A-31AA-A Forward section - Main gearbox rod attachment struc- ture - Detailed inspection 39-A-53-10-00-00A-31AB-A Forward section - Anti-torque beam attachment struc- ture - Detailed inspection 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 2 39-A-53-10-00-00A-31AE-A Forward section - Engine attachment internal backup structure - Detailed inspection 39-A-53-10-00-00A-31AV-A Forward section - Frame STA 5700 - Detailed inspection 39-A-53-10-00-00A-31AW-A Forward section - Rescue hoist external backup struc- ture - Detailed inspection 39-A-53-10-00-00A-31AX-A Forward section - Double rescue hoist external backup structure - Detailed inspection 39-A-53-10-00-00A-31AY-A Forward section - Single rescue hoist external backup structure - Detailed inspection 39-A-53-40-00-00A-31AA-A Tail section - Fin rib attachment - Detailed inspection 39-A-53-40-00-00A-31AB-A Tail section - Detailed inspection 39-A-53-40-00-00A-31AC-A Tail section - Tail gearbox attachment structure - Detailed inspection 39-A-53-40-00-00A-31AG-A Tail section - Tail/rear fuselage attachment fittings - Detailed inspection 39-A-53-40-00-00A-31AH-A Tail section - Aft spar to skin joint - Detailed inspection 39-A-62-11-00-00A-310A-A Main rotor blade installation - Blades - General visual inspection 39-A-62-11-01-00A-31AB-A Main rotor blade - Detailed inspection 39-A-62-22-00-00A-31AC-A Main rotor head - Elastomeric bearings - Detailed inspection 39-A-62-22-00-00A-31AF-A Main rotor head - Main rotor hub - Detailed inspection 39-A-62-31-06-00A-31AA-A Swashplate - Rotating swashplate and duplex bearing attaching parts - Detailed inspection 39-A-64-11-00-00A-310A-A Tail rotor blade installation - Blades - General visual inspection 39-A-64-11-00-00A-31AB-A Tail rotor blade installation - Elastomeric bearings - Detailed inspection 39-A-64-21-00-00A-31AD-A Tail rotor head installation - Lag damper elastomer - Detailed inspection 39-A-75-51-00-00A-31AA-K Engine inlet particle separator system - Number 1 and Number 2 main panels - Detailed inspection 39-B-53-10-00-00A-31AB-K Forward section - Frame STA 5700 - Detailed inspection 39-B-53-10-00-00A-31BA-K Forward section - Main landing gear backup structures - Special detailed inspection 39-B-62-11-01-00A-31AA-A Main rotor blade - Detailed inspection Table 1 References (Continued) Data module/Technical publication Title 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 3 10 Description 1 Introduction The parts listed in the following schedule must be mandatorily inspected when the indicated interval is reached. 2 Affected parts Refer to Table 2 - Mandatory inspections - List of affected parts. 3 Terms and definitions of Table 2 3.1 Reference (Ref) This column gives the unique reference [MI (Mandatory Inspections) plus the system number fol- lowed by a progressive number] which identifies the part. 3.2 Part This column gives the part. 3.3 Task This column gives the description of the inspection to perform. 3.4 Interval This column gives the inspection interval for the part. Unless otherwise specified, the inspection interval is in Flying Hours (FH). Flying hours are defined as those hours accumulated from take- off to landing. The inspection intervals of some parts are expressed in “landings” because their inspection inter- vals are dependent upon the rotor start-stop cycles and the helicopter ground-air-ground cycles. Inspection intervals are mandatory and cannot be increased. Inspection intervals can be antici- pated provided that the next inspections intervals do not exceed the values mandated in this chapter. Example: – Task interval: 100 FH. If task is performed at 85 FH, next task must be performed within 100 FH from the previous compliance. 3.5 Reference (DMC) This column shows the Data Module Code which provides the instructions to perform the inspec- tion. 39-C-64-21-00-00A-31AA-A Tail rotor head installation - Elastomeric lag damper - Detailed inspection 39-C-64-21-00-00A-31AB-A Tail rotor head installation - Elastomeric lag damper rod- end - Detailed inspection Table 1 References (Continued) Data module/Technical publication Title 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 4 Table 2 Mandatory inspections - List of affected parts Ref Part Task Interval Reference (DMC) MI25-01 D-Lock External Hoist Hook General visual inspection for dam- age Daily 39-A-25-91-01-01A-310A-K MI53-01 TGB Fitting (fasteners in skin and spar) Detailed inspection for cracks (both inter- nal and external sides) 300 39-A-53-40-00-00A-31AC-A MI53-02 Main Landing Gear LH Panel General visual inspection for dam- age 300 39-A-53-10-00-00A-310A-A MI53-03 Main Landing Gear RH Panel General visual inspection for dam- age 300 39-A-53-10-00-00A-310A-A MI53-04 Tail Structure Assem- bly (fin rib attachment area) Detailed inspection for cracks (both inter- nal and external sides) 100 39-A-53-40-00-00A-31AA-A MI53-05 Tail Structure Assem- bly (tail cone RH/LH panels upper and lower joint) Detailed inspection for cracks (both inter- nal and external sides) 300 39-A-53-40-00-00A-31AB-A MI53-06 Tail Structure Assem- bly (tail cone joint STA 11020) Detailed inspection for cracks (both inter- nal and external sides) 300 39-A-53-40-00-00A-31AB-A MI53-07 Fuselage Structure Assembly (forward MGB rod backup structure) Detailed inspection for cracks 300 (Note 11) 39-A-53-10-00-00A-31AA-A MI53-08 Fuselage Structure Assembly (aft MGB rod backup structure and fitting part number 3P5330A11251) Detailed inspection for cracks 300 (Note 8) (Note 10) 39-A-53-10-00-00A-31AA-A MI53-09 Fuselage Structure Assembly (antitorque beam backup struc- ture) Detailed inspection for cracks 1300 39-A-53-10-00-00A-31AB-A MI53-10 Tail Structure Assem- bly (tail/rear fuselage attachment fittings) Detailed inspection for cracks 200 (Note 13) 39-A-53-40-00-00A-31AG-A 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 5 10 MI53-11 Tail Structure Assem- bly (aft/front spar to skin joint) Detailed inspection for cracks (both inter- nal and external sides) 100 39-A-53-40-00-00A-31AH-A MI53-12 Fuselage Structure Assembly (frame STA 5700, RH/LH side) Detailed inspection for cracks 100 (Note 5) (Note 6) (Note 7) 39-A-53-10-00-00A-31AV-A MI53-13 Internal Engine Attachment Backup Structure Detailed inspection for cracks 1200 39-A-53-10-00-00A-31AE-A MI53-14 Fuselage Structure Assembly (external hoist backup struc- ture) (Note 3) Detailed inspection for cracks 4000 External Hoist Lifts (see Para 4 ) 39-A-53-10-00-00A-31AW-A MI53-14 Fuselage Structure Assembly (external hoist backup struc- ture) (Note 4) Detailed inspection for cracks 4000 External Hoist Lifts (see Para 4 ) 39-A-53-10-00-00A-31AX-A 39-A-53-10-00-00A-31AY-A MI53-15 Main landing gear backup structure LH/ RH side (Goodrich landing gear installa- tion) Special detailed inspection for cracks (by using eddy cor- rent inspection method) 1250 Landings 39-B-53-10-00-00A-31BA-K MI53-16 Fuselage Structure Assembly (frame STA 5700, LH/RH side, lower area) (Goodrich landing gear installa- tion) Detailed inspection for cracks (nut and washer removal required only in the lowest attaching posi- tion) 7000 Landings 39-B-53-10-00-00A-31AB-K MI62-01 Main Rotor Blade Assembly General visual inspection for dam- age 50 (Note 2) 39-A-62-11-00-00A-310A-A MI62-02 Main Rotor Elasto- meric Bearing (part number 3G6220V00153) Detailed inspection for cracks in the elas- tomer 50 39-A-62-22-00-00A-31AC-A MI62-03 Main Rotor Elasto- meric Bearing (part number 3G6220V00154) Detailed inspection for cracks in the elas- tomer 50 39-A-62-22-00-00A-31AC-A MI62-04 Main Rotor Hub Assembly Detailed inspection (without removal of blades) 2500 39-A-62-22-00-00A-31AF-A Table 2 Mandatory inspections - List of affected parts Ref Part Task Interval Reference (DMC) 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 6 MI62-05 Deleted MI62-06 Main Rotor Rotating Swashplate Inspection for integ- rity and loss of torque of the bolts and ring retaining the duplex bearing 402 (Note 12) 39-A-62-31-06-00A-31AA-A MI62-07 Main Rotor Blade Assembly with Heater Mat (part number 4G6210A00132) Detailed inspection (hammer tapping) of the bonding area between tip cap and blade (from STA 6300 to STA 6400) for debondings and/or delaminations (blade removal not required) 100 39-B-62-11-01-00A-31AA-A MI62-08 Main Rotor Blade Assembly (part num- ber 3G6210A00131) Detailed inspection (hammer tapping) of the bonding area between tip cap and blade (from STA 6300 to STA 6400) for debondings and/or delaminations (blade removal not required) 100 (Note 9) 39-A-62-11-01-00A-31AB-A MI64-01 Tail Rotor Blade Assembly General visual inspection for dam- age 50 (Note 2) 39-A-64-11-00-00A-310A-A MI64-02 Tail Rotor Elastomeric Spherical Bearing (part number 3G6420V00153) Detailed inspection for cracks in the elas- tomer 100 39-A-64-11-00-00A-31AB-A MI64-03 Tail Rotor Elastomeric Spherical Bearing (part number 3G6420V00154) Detailed inspection for cracks in the elas- tomer 25 39-A-64-11-00-00A-31AB-A MI64-04 Tail Rotor Damper Detailed inspection for cracks in the elas- tomer 100 39-A-64-21-00-00A-31AD-A MI64-05 Tail Rotor Damper (part number 3G6420V00851) Detailed inspection of rod end for cracks in the elastomer 200 39-C-64-21-00-00A-31AB-A MI64-06 Tail Rotor Damper (part number 3G6420V00851) Detailed inspection of body for cracks in the elastomer 300 39-C-64-21-00-00A-31AA-A Table 2 Mandatory inspections - List of affected parts Ref Part Task Interval Reference (DMC) 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 7 10 MI71-00 Engine Air Particle Separator Left and Right Main Panels (part numbers 3G7160V00551 and 3G7160V00651) Detailed inspection for cracks in the pan- els 25 39-A-75-51-00-00A-31AA-K Notes 1 Deleted. 2 Rotor Starting or Stopping with wind speed above 33 kts. For each Rotor Start or Stop performed with wind speed above 33 kts the additional inspections reported in Table 6 - Rotor Starting or Stopping with wind speed above 33 kts - Additional inspections must be mandatorily carried out. 3 Helicopters AW139 that have the Breeze rescue hoist system installed. 4 Helicopters AW139 that have the Goodrich rescue hoist system installed. 5 The 100 FH interval is extended to 1200 FH if the retro modification P/N 3G5306P08512 is applied to the frames P/N 3P5338A13352 (LH) and 3P5338A13452 (RH). 6 The inspection requirement is not applicable to helicopters that install the following frame P/N: 3P5338A13354 (LH) and 3P5338A13454 (RH). 7 The 100 FH interval is extended to 1200 FH if the retro modification P/N 3G5306P08513 is applied to the frames P/N 3P5338A13353 (LH) and 3P5338A13453 (RH). 8 When the 3750 FH are reached, the 300 FH interval is reduced to 150 FH if the retro modifica- tion P/N 3G5306P36711 or P/N 3G5306P39211 is not applied. 9 The inspection requirement is applicable to Main Rotor Blade Assembly part number 3G6210A00131 when the 10000 FH are reached. 10 The 300 FH interval is extended up to 1300 FH if the Fuselage Structure assembly P/N 3G5300X00135 or the Cruciform fitting retromodification P/N 3G5306P36711 are installed on the rotorcraft. 11 The 300 FH interval is extended up to 1300 FH for all helicopters except S/N from 31003 to 31011. 12 The inspection requirement is not applicable to helicopters that install the Main Rotor Rotating Swashplate P/N 3G6230A00333. 13 The 200 FH interval is extended to 8350 landings for the following configurations: - Tail assembly P/N 3G5350A00136 - Tail assembly P/N 3G5350A00135 plus retromodification P/N 3G5309P02711 (Part I of Optional BT 139-419) - Rear Fuselage Assy P/N 3P5340A00134 or P/N 3G5340A11131 - Rear Fuselage assembly P/N 3P5340A00132 or 3P5340A00133 plus retromodification P/N 3G5306P38811 (Optional BT 139-418) Table 2 Mandatory inspections - List of affected parts Ref Part Task Interval Reference (DMC) 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 8 - Tail assembly P/N 3G5350A00134 or P/N 3G5350A00133 or P/N 3G5350A00132 plus the fol- lowing retromodifications: 1 P/N 3G5309P02711 (Part I of Optional BT 139-419) 2 P/N 3G5309P01812 (Optional BT 139-200) Table 3 Mandatory inspections - Rescue hoist system (Breeze) Ref Part Task Interval Reference (DMC) MI25-02 Rescue hoist GVI of entire usable length of the cable for damage and condi- tion Prior the first use of the day 39-A-25-91-01-00A-310A-K Table 4 Mandatory inspections - Double rescue hoist system (Goodrich) Ref Part Task Interval Reference (DMC) MI25-03 Rescue hoist cable Do a GVI of the maxi- mum length of cable used during the day operation for dam- age and condition After the last flight of the day or before the first flight of the day if the res- cue hoist is used or it is envisaged to be used 39-A-25-94-01-00A-310A-K Table 5 Mandatory inspections - Single rescue hoist system (Goodrich) Ref Part Task Interval Reference (DMC) MI25-04 Rescue hoist cable Do a GVI of the maxi- mum length of cable used during the day operation for dam- age and condition After the last flight of the day or before the first flight of the day if the res- cue hoist is used or it is envisaged to be used 39-A-25-96-01-00A-310A-K Table 6 Rotor Starting or Stopping with wind speed above 33 kts - Additional inspections Ref Part Task Interval Reference (DMC) MI62-01 Main Rotor Blade Assembly General visual inspection for dam- age Within 15 FH from the event 39-A-62-11-00-00A-310A-A Table 2 Mandatory inspections - List of affected parts Ref Part Task Interval Reference (DMC) 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 9 10 4 External hoist lift The external hoist lift is defined as an unreeling and recovery of the cable with a load attached to the hook, independent of the length of the cable that is deployed/recovered. An unreeling/recovery of the cable with no load on the hook is not considered to be a lift. Any operation where a load is applied for half the operation (i.e. unreeling or recovery) must be considered as one lift. MI64-01 Tail Rotor Blade Assembly General visual inspection for dam- age Within 15 FH from the event 39-A-64-11-00-00A-310A-A Table 6 Rotor Starting or Stopping with wind speed above 33 kts - Additional inspections Ref Part Task Interval Reference (DMC) 39-A-AMPI-00-P Applicable to: All 39-A-04-20-00-00A-028E-P 2018-02-15 Page 10 THIS PAGE INTENTIONALLY LEFT BLANK