Airworthiness Directives; Airbus Helicopters, 50226-50230 [2021-19247]

Download as PDF 50226 § 39.13 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–16–16 Airbus Helicopters: Amendment 39–21679; Docket No. FAA–2021–0449; Project Identifier 2018–SW–001–AD. (a) Effective Date This airworthiness directive (AD) is effective October 13, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, and AS350D helicopters; and Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, certificated in any category, with litter kits installed having any part number specified in paragraphs (c)(1) through (3) of this AD: (1) Part number (P/N) 350–200034 (lefthand litter kit). (2) P/N 350–200194 (left-hand litter kit). (3) P/N 350–200144 (right-hand litter kit). (d) Subject Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft Flight Control. (e) Unsafe Condition This AD was prompted by reports that the lanyards (bead chain tethers), which hold the quick release pins to the forward bracket assembly of certain litter kits, can loop around the directional control pedal stubs, limiting the movement of the pedals, which affect the control of the flight. The FAA is issuing this AD to address interference between the litter kit lanyards and the flight controls. The unsafe condition, if not addressed, could result in limited flight control movement and difficulty controlling the helicopter. jbell on DSKJLSW7X2PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For litter kits having any part specified in paragraphs (c)(1) through (3) of this AD: Prior to each flight until the modification required by paragraph (g)(2) of this AD is accomplished, do a pre-flight check to determine if there is interference (e.g. limited movement of the pedals due to the lanyards that hold the quick release pins to the forward bracket assembly being looped around the directional control pedal stubs) between the lanyards that hold the quick release pins to the forward bracket assembly and the pedals. If interference is found, before further flight, do the modification required by paragraph (g)(2) of this AD for the affected litter kit. The pre-flight check may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with VerDate Sep<11>2014 16:25 Sep 07, 2021 Jkt 253001 this AD in accordance with § 43.9(a)(1) through (4) and § 91.417(a)(2)(v). The record must be maintained as required by § 91.417, § 121.380, or § 135.439. (2) Within 25 hours time-in-service (TIS) after the effective date of this AD, modify the attachment location of the lanyard for litter kits having any part specified in paragraphs (c)(1) through (3) of this AD. Do the modification in accordance with paragraph 3.B.2., ‘‘Procedure,’’ of the Accomplishment Instructions of Airbus Helicopters Service Bulletin SB–AHCA–128, Revision 0, dated March 24, 2017. Note 1 to paragraph (g): Litter kits, P/N 350–200034 and P/N 350–200194, may have been installed under supplemental type certificate (STC) SR00406NY (for Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters) or STC SR00407NY (for Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, and AS350D helicopters). Litter kit P/N 350–200144 may have been installed under STC SR00458NY (for Model AS350BA, AS350B2, and AS350B3 helicopters). (h) Parts Installation Limitation As of the effective date of this AD, no person may install a litter kit having a part number identified in paragraphs (c)(1) through (3) of this AD, on any helicopter, unless the installation is modified as required by paragraph (g)(2) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Helicopters Service Bulletin SB– AHCA–128, Revision 0, dated March 24, 2017. (ii) [Reserved] (3) For service information identified in this AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. (4) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. Issued on July 30, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (j) Related Information (1) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 1600 Stewart Ave., Mail Stop: Room 410, Westbury, NY 11590; telephone (516) 228–7330; email andrea.jimenez@faa.gov. (2) For information about AMOCs, contact the Manager, International Validation Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-AVS-AIR-730-AMOC@faa.gov. (3) The subject of this AD is addressed in Transport Canada AD CF–2017–37 dated December 19, 2017. You may view the Transport Canada AD at https:// www.regulations.gov in Docket No. FAA– 2021–0449. Airworthiness Directives; Airbus Helicopters PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 [FR Doc. 2021–19252 Filed 9–7–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0379; Project Identifier MCAI–2021–00068–R; Amendment 39–21667; AD 2021–16–05] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2016–12– 51, which applied to all Airbus Helicopters Model AS332L2 and Model EC225LP helicopters. AD 2016–12–51 prohibited all further flight of Model AS332L2 and Model EC225LP helicopters. This AD requires replacing certain second stage planet gear assemblies, removing certain epicyclic modules, installing a full flow magnetic plug (FFMP), revising the existing SUMMARY: E:\FR\FM\08SER1.SGM 08SER1 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations jbell on DSKJLSW7X2PROD with RULES rotorcraft flight manual (RFM) for your helicopter, repetitively inspecting the main gearbox (MGB) particle detectors, repetitively inspecting the MGB oil filter and oil cooler, and corrective action if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The actions specified in this AD terminate the flight prohibition. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 13, 2021. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 13, 2021. ADDRESSES: For EASA material incorporated by reference (IBR) in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this material on the EASA website at https:// ad.easa.europa.eu. For Airbus Helicopters service information, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 817–222–5110. It is also available in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0379. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0379; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Mahmood Shah, Aviation Safety Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222– 5538; email mahmood.g.shah@faa.gov. SUPPLEMENTARY INFORMATION: VerDate Sep<11>2014 16:25 Sep 07, 2021 Jkt 253001 Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017– 0134R2, dated April 16, 2020 (EASA AD 2017–0134R2) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for all Airbus Helicopters Model AS332L2 and EC225LP helicopters. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2016–12–51, Amendment 39–18578 (81 FR 43479, July 5, 2016) (AD 2016–12–51). AD 2016–12–51 applied to all Airbus Helicopters Model AS332L2 and EC225LP helicopters. The NPRM published in the Federal Register on June 1, 2021 (86 FR 29212). The NPRM was prompted by an accident involving an Airbus Helicopters Model EC225LP helicopter in which the main rotor hub detached from the MGB. The Airbus Helicopters Model AS332L2 helicopter has a similar design to the affected Model EC225LP helicopter, therefore, this model may be subject to the unsafe condition revealed on the Model EC225LP helicopter. The NPRM proposed to require replacing certain second stage planet gear assemblies, removing certain epicyclic modules, installing an FFMP, revising the existing RFM for your helicopter, repetitively inspecting the MGB particle detectors, repetitively inspecting the MGB oil filter and oil cooler, and corrective action if necessary, as specified in EASA AD 2017–0134R2. The NPRM also proposed to provide terminating action for certain repetitive inspections. The FAA is issuing this AD to address failure of the main rotor system, which would result in loss of control of the helicopter. See the MCAI for additional background information. Discussion of Final Airworthiness Directive Comments The FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public. Conclusion The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 50227 • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 EASA AD 2017–0134R2 references procedures for replacing certain second stage planet gear assemblies with serviceable parts; removing certain epicyclic modules from service; modifying the helicopter by installing an FFMP; revising the RFM to prohibit MGB particle burning in-flight; repetitively inspecting the FFMP and MGB particle detectors for metal particles, analyzing any metal particles that are found, and corrective action; and repetitively inspecting the MGB oil filter and oil cooler for particles and corrective action. The corrective actions include replacing an affected MGB with a serviceable MGB. EASA AD 2017– 0134R2 also provides terminating action for certain repetitive inspections. Airbus Helicopters has issued Emergency Alert Service Bulletin 05A049, Revision 6, dated July 25, 2017, for Model EC225 helicopters; and Emergency Alert Service Bulletin 05.01.07, Revision 6, dated July 27, 2017, for Model AS332 helicopters. The service information specifies procedures for, among other things, replacing the MGB. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Differences Between This AD and the MCAI Although the service information referenced in EASA AD 2017–0134R2 specifies to return affected planetary gear assemblies to the manufacturer for module overhaul, this AD does not include that requirement. Although the service information referenced in EASA AD 2017–0134R2 specifies that retrofit of the planet gear of the MGB can only be done by Airbus Helicopters or Airbus Helicopters approved repair centers, this AD does not include that requirement. EASA AD 2017–0134R2 requires operators to ‘‘inform all flight crews’’ of revisions to the RFM, and thereafter to ‘‘operate the helicopter accordingly.’’ However, this AD does not specifically require those actions. FAA regulations mandate compliance with only the operating limitations section of the flight manual. The flight manual changes required by this AD apply to the emergency procedures section of the existing RFM for your helicopter. Furthermore, compliance with such E:\FR\FM\08SER1.SGM 08SER1 50228 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations requirements in an AD is impracticable to demonstrate or track on an ongoing basis; therefore, a requirement to operate the aircraft in such a manner is unenforceable. Nonetheless, the FAA recommends that flight crews of the helicopters listed in the applicability operate in accordance with the revised emergency procedures mandated by this AD. Interim Action The FAA considers this AD interim action. If final action is later identified, the FAA might consider further rulemaking then. Costs of Compliance The FAA estimates that this AD affects 28 helicopters of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS * Parts cost Action Labor cost New actions ............................................ Up to 6 work-hours × $85 per hour = $510. Cost per product $0 Up to $510 ............. Cost on U.S. operators Up to $14,280. * Table does not include estimated costs for reporting. The FAA estimates that it will take about 1 work-hour per product to comply with the reporting requirement in this AD. The average labor rate is $85 per hour. Based on these figures, the FAA estimates the cost of reporting the inspection results on U.S. operators to be $2,380, or $85 per product. The FAA estimates the following costs to do any necessary on-condition actions that will be required based on the results of any required actions. The FAA has no way of determining the number of helicopters that might need these on-condition actions: ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product 40 work-hours × $85 per hour = $3,400 ................................................................................................................. $295,000 $298,400 According to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators. As a result, the FAA has included all known costs in the cost estimate. jbell on DSKJLSW7X2PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Pkwy., Fort Worth, TX 76177– 1524. VerDate Sep<11>2014 16:25 Sep 07, 2021 Jkt 253001 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Fmt 4700 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Frm 00016 List of Subjects in 14 CFR Part 39 ■ Regulatory Findings PO 00000 For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Sfmt 4700 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive 2016–12–51, Amendment 39–18578 (81 FR 43479, July 5, 2016); and ■ b. Adding the following new airworthiness directive: ■ ■ E:\FR\FM\08SER1.SGM 08SER1 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 2021–16–05 Airbus Helicopters: Amendment 39–21667; Docket No. FAA–2021–0379; Project Identifier MCAI–2021–00068–R. (a) Effective Date This airworthiness directive (AD) is effective October 13, 2021. (b) Affected ADs This AD replaces AD 2016–12–51, Amendment 39–18578 (81 FR 43479, July 5, 2016) (AD 2016–12–51). (c) Applicability This AD applies to all Airbus Helicopters Model AS332L2 and EC225LP helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 6320, Main Rotor Gearbox. (e) Reason This AD was prompted by an accident involving a Model EC225LP helicopter in which the main rotor hub detached from the main gearbox. The FAA is issuing this AD to address failure of the main rotor system, which would result in loss of control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. jbell on DSKJLSW7X2PROD with RULES (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2017–0134R2, dated April 16, 2020 (EASA AD 2017– 0134R2). (h) Exceptions to EASA AD 2017–0134R2 (1) Where EASA AD 2017–0134R2 refers to the effective dates specified in paragraphs (h)(1)(i) through (v) of this AD, this AD requires using the effective date of this AD. (i) The effective date of EASA AD 2017– 0134R2. (ii) October 13, 2016 (the effective date of EASA AD 2016–0199, dated October 7, 2016). (iii) March 20, 2017 (the effective date of EASA AD 2017–0050–E, dated March 17, 2017). (iv) June 30, 2017 (the effective date of EASA AD 2017–0111, dated June 23, 2017). (v) August 1, 2017 (the effective date of EASA AD 2017–0134, dated July 27, 2017). (2) The ‘‘Remarks’’ section of EASA AD 2017–0134R2 does not apply to this AD. (3) Where any service information referred to in EASA AD 2017–0134R2 specifies to discard certain parts after they have been removed from the helicopter, this AD requires removing those parts from service. (4) Where paragraph (2) of EASA AD 2017– 0134R2 specifies to replace a part before exceeding the applicable ‘‘new service life limit,’’ this AD requires removing that part from service. (5) Where any service information referred to in EASA AD 2017–0134R2 specifies to VerDate Sep<11>2014 16:25 Sep 07, 2021 Jkt 253001 return certain parts to the manufacturer, including for overhaul, after they have been removed from the helicopter, this AD does not include that requirement. (6) Where EASA AD 2017–0134R2 refers to flight hours (FH), this AD requires using hours time-in-service. (7) Where any service information referred to in EASA AD 2017–0134R2 specifies to perform a metallurgical analysis and contact the manufacturer if unsure about the characterization of the particles collected, this AD does require characterization of the particles collected, however this AD does not require contacting the manufacturer to determine the characterization of the particles collected. (8) Where EASA AD 2017–0134R2 requires actions during each ‘‘after last flight’’ of the day (ALF) inspection, this AD requires those actions before the first flight of each day. (9) Where any service information referred to in EASA AD 2017–0134R2 specifies to do the actions identified in paragraphs (h)(9)(i) through (iv) of this AD, this AD does not include those requirements. (i) Watch a video for removing the grease from the full flow magnetic plug (FFMP), using a cleaning agent, and collecting particles. (ii) Return affected planetary gear assembly to the manufacturer for module overhaul. (iii) Contact the approved repair station/ Airbus Helicopters if the reason for a repair to an epicyclic module is unknown and inform/contact Airbus Helicopters. (iv) Contact the approved repair station/ Airbus Helicopters depending on who performed the last overhaul (RG) to determine if a repair has been done on the second stage planet gears since new. (10) Where any service information referred to in EASA AD 2017–0134R2 specifies that retrofit of the planet gear of the main gearbox (MGB) can only be done by Airbus Helicopters or Airbus Helicopters approved repair centers, this AD does not require that the retrofit of the planet gear be done only by Airbus Helicopters or Airbus Helicopters approved repair centers. For this AD the retrofit can also be done by an FAAapproved repair station. (11) Where paragraph (5) of EASA AD 2017–0134R2 specifies accomplishing the FFMP additional work within 3 months after August 1, 2017, this AD requires accomplishing the FFMP additional work within 4 months after the effective date of this AD. (12) Where paragraph (6) of EASA AD 2017–0134R2 specifies to ‘‘inform all flight crews and, thereafter, operate the helicopter accordingly,’’ this AD does not require those actions. (13) Where any service information referred to in EASA AD 2017–0134R2 specifies that if any 16NCD13 particles are found you are to take a 1-liter sample of oil and send it to the manufacturer, this AD does not require those actions. (14) Where any service information referred to in EASA AD 2017–0134R2 specifies ‘‘Do not resume flights until corrective action(s) are agreed by Airbus Helicopters,’’ or to contact Airbus Helicopters before resuming flights ‘‘if PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 50229 further particles are collected during the close monitoring period’’ for this AD, you must repair before further flight using a method specified in paragraph (h)(14)(i) or (ii) of this AD. (i) In accordance with FAA approved procedures. (ii) The procedures specified in Appendix 4.A., Particle Analysis, of Airbus Helicopters Emergency Alert Service Bulletin 05A049, Revision 6, dated July 25, 2017; or Emergency Alert Service Bulletin 05.01.07, Revision 6, dated July 27, 2017, as applicable, except as required by paragraphs (h)(5), (7), and (13) of this AD. (15) Where the service information identified in EASA AD 2017–0134R2 specifies to report inspection results to Airbus Helicopters, for this AD, report the inspection results at the applicable time specified in paragraph (h)(15)(i) or (ii) of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the date of the inspection. (ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (i) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraph (4) of EASA AD 2017–0134R2, if those actions were performed before the effective date of this AD using Airbus Helicopters Emergency Alert Service Bulletin 63.00.83 or 63A030, both Revision 1, both dated October 7, 2016. (2) Corrective action(s) for the inspections required by paragraphs (8) and (10) of EASA AD 2017–0134R2 accomplished on a helicopter before the effective date of this AD, in accordance with Paragraph 3.B. and Appendix 4.A. of the Accomplishment Instructions of the applicable Airbus Helicopters service information specified in paragraphs (i)(2)(i) through (viii) of this AD, as applicable, are acceptable to comply with the requirements of paragraph (11) of EASA AD 2017–0134R2 for that helicopter, but only for the corrective actions for the inspections required by paragraphs (8) and (10) of EASA AD 2017–0134R2. (i) Emergency Alert Service Bulletin 05.01.07, Revision 2, dated October 7, 2016. (ii) Emergency Alert Service Bulletin 05.01.07, Revision 3, dated February 25, 2017. (iii) Emergency Alert Service Bulletin 05.01.07, Revision 4, dated March 17, 2017. (iv) Emergency Alert Service Bulletin 05.01.07, Revision 5, dated June 23, 2017. (v) Emergency Alert Service Bulletin 05A049, Revision 2, dated October 7, 2016. (vi) Emergency Alert Service Bulletin 05A049, Revision 3, dated February 25, 2017. (vii) Emergency Alert Service Bulletin 05A049, Revision 4, dated March 17, 2017. (viii) Emergency Alert Service Bulletin 05A049, Revision 5, dated June 23, 2017. (j) Special Flight Permit Special flight permits, as described in 14 CFR 21.197 and 21.199, are prohibited. E:\FR\FM\08SER1.SGM 08SER1 jbell on DSKJLSW7X2PROD with RULES 50230 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. (l) Related Information (1) For more information about this AD, contact Mahmood Shah, Aviation Safety Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5538; email mahmood.g.shah@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(4) and (5) of this AD. 14 CFR Part 39 16:25 Sep 07, 2021 Jkt 253001 [FR Doc. 2021–19247 Filed 9–7–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2021–0198; Project Identifier MCAI–2020–00950–E; Amendment 39–21695; AD 2021–17–12] RIN 2120–AA64 (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2017–0134R2, dated April 16, 2020. (ii) Airbus Helicopters Emergency Alert Service Bulletin 05A049, Revision 6, dated July 25, 2017. (iii) Airbus Helicopters Emergency Alert Service Bulletin 05.01.07, Revision 6, dated July 27, 2017. (3) For EASA AD 2017–0134R2, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; Internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. (4) For Airbus Helicopters service information, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. (5) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 817–222–5110. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0379. (6) You may view this material that is incorporated by reference at the National VerDate Sep<11>2014 Issued on July 22, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by RollsRoyce plc) Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2020–13– 07 for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000–D2, Trent 1000–J2, and Trent 1000–K2 model turbofan engines with a certain partnumbered fuel pump installed. AD 2020–13–07 required removal and replacement of the fuel pump with a part eligible for installation. This AD was prompted by the manufacturer’s investigation into an unexpected reduction in fuel pump performance in certain high life fuel pumps and subsequent determination that an additional part-numbered fuel pump is subject to the same unsafe condition. This AD requires new and reduced life limits for certain part-numbered fuel pumps, depending on the engine model the fuel pump is installed on. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 13, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 13, 2021. ADDRESSES: For service information identified in this final rule, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; phone: +44 (0)1332 242424; website: https:// SUMMARY: PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 www.rolls-royce.com/contact-us.aspx. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238–7759. It is also available at http://www.regulations.gov by searching for and locating Docket No. FAA–2021–0198. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0198; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kevin M. Clark, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7088; fax: (781) 238– 7199; email: kevin.m.clark@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2020–13–07, Amendment 39–21152 (85 FR 38312, June 26, 2020), (AD 2020–13–07). AD 2020–13–07 applied to all RRD Trent 1000–D2, Trent 1000–J2, and Trent 1000–K2 model turbofan engines with fuel pump, part number G5030FPU01, installed. The NPRM published in the Federal Register on March 30, 2021 (86 FR 16548). The NPRM was prompted by the manufacturer’s investigation into an unexpected reduction in fuel pump performance in certain high life fuel pumps and life-related wear-out of the internal components and subsequent determination that an additional partnumbered fuel pump is subject to this same unsafe condition. In the NPRM, the FAA proposed to retain all the requirements of AD 2020–13–07. In the NPRM, the FAA also proposed to add an additional part-numbered fuel pump and additional Trent 1000 model turbofan engines on which this fuel pump is installed to the applicability. In the NPRM, the FAA also proposed to require new and reduced life limits for certain part-numbered fuel pumps, E:\FR\FM\08SER1.SGM 08SER1

Agencies

[Federal Register Volume 86, Number 171 (Wednesday, September 8, 2021)]
[Rules and Regulations]
[Pages 50226-50230]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-19247]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0379; Project Identifier MCAI-2021-00068-R; 
Amendment 39-21667; AD 2021-16-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-12-
51, which applied to all Airbus Helicopters Model AS332L2 and Model 
EC225LP helicopters. AD 2016-12-51 prohibited all further flight of 
Model AS332L2 and Model EC225LP helicopters. This AD requires replacing 
certain second stage planet gear assemblies, removing certain epicyclic 
modules, installing a full flow magnetic plug (FFMP), revising the 
existing

[[Page 50227]]

rotorcraft flight manual (RFM) for your helicopter, repetitively 
inspecting the main gearbox (MGB) particle detectors, repetitively 
inspecting the MGB oil filter and oil cooler, and corrective action if 
necessary, as specified in a European Union Aviation Safety Agency 
(EASA) AD, which is incorporated by reference. The actions specified in 
this AD terminate the flight prohibition. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective October 13, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 13, 
2021.

ADDRESSES: For EASA material incorporated by reference (IBR) in this 
AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 8999 000; email [email protected]; internet 
www.easa.europa.eu. You may find this material on the EASA website at 
https://ad.easa.europa.eu. For Airbus Helicopters service information, 
contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at https://www.airbus.com/helicopters/services/technical-support.html. You may view this material at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177. For information on the availability of this 
material at the FAA, call 817-222-5110. It is also available in the AD 
docket on the internet at https://www.regulations.gov by searching for 
and locating Docket No. FAA-2021-0379.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0379; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Mahmood Shah, Aviation Safety 
Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, 
TX 76177; telephone 817-222-5538; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2017-0134R2, dated April 16, 2020 
(EASA AD 2017-0134R2) (also referred to as the Mandatory Continuing 
Airworthiness Information, or the MCAI), to correct an unsafe condition 
for all Airbus Helicopters Model AS332L2 and EC225LP helicopters.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2016-12-51, Amendment 39-18578 (81 FR 
43479, July 5, 2016) (AD 2016-12-51). AD 2016-12-51 applied to all 
Airbus Helicopters Model AS332L2 and EC225LP helicopters. The NPRM 
published in the Federal Register on June 1, 2021 (86 FR 29212). The 
NPRM was prompted by an accident involving an Airbus Helicopters Model 
EC225LP helicopter in which the main rotor hub detached from the MGB. 
The Airbus Helicopters Model AS332L2 helicopter has a similar design to 
the affected Model EC225LP helicopter, therefore, this model may be 
subject to the unsafe condition revealed on the Model EC225LP 
helicopter. The NPRM proposed to require replacing certain second stage 
planet gear assemblies, removing certain epicyclic modules, installing 
an FFMP, revising the existing RFM for your helicopter, repetitively 
inspecting the MGB particle detectors, repetitively inspecting the MGB 
oil filter and oil cooler, and corrective action if necessary, as 
specified in EASA AD 2017-0134R2. The NPRM also proposed to provide 
terminating action for certain repetitive inspections.
    The FAA is issuing this AD to address failure of the main rotor 
system, which would result in loss of control of the helicopter. See 
the MCAI for additional background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
except for minor editorial changes. The FAA has determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    EASA AD 2017-0134R2 references procedures for replacing certain 
second stage planet gear assemblies with serviceable parts; removing 
certain epicyclic modules from service; modifying the helicopter by 
installing an FFMP; revising the RFM to prohibit MGB particle burning 
in-flight; repetitively inspecting the FFMP and MGB particle detectors 
for metal particles, analyzing any metal particles that are found, and 
corrective action; and repetitively inspecting the MGB oil filter and 
oil cooler for particles and corrective action. The corrective actions 
include replacing an affected MGB with a serviceable MGB. EASA AD 2017-
0134R2 also provides terminating action for certain repetitive 
inspections.
    Airbus Helicopters has issued Emergency Alert Service Bulletin 
05A049, Revision 6, dated July 25, 2017, for Model EC225 helicopters; 
and Emergency Alert Service Bulletin 05.01.07, Revision 6, dated July 
27, 2017, for Model AS332 helicopters. The service information 
specifies procedures for, among other things, replacing the MGB.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

Differences Between This AD and the MCAI

    Although the service information referenced in EASA AD 2017-0134R2 
specifies to return affected planetary gear assemblies to the 
manufacturer for module overhaul, this AD does not include that 
requirement.
    Although the service information referenced in EASA AD 2017-0134R2 
specifies that retrofit of the planet gear of the MGB can only be done 
by Airbus Helicopters or Airbus Helicopters approved repair centers, 
this AD does not include that requirement.
    EASA AD 2017-0134R2 requires operators to ``inform all flight 
crews'' of revisions to the RFM, and thereafter to ``operate the 
helicopter accordingly.'' However, this AD does not specifically 
require those actions. FAA regulations mandate compliance with only the 
operating limitations section of the flight manual. The flight manual 
changes required by this AD apply to the emergency procedures section 
of the existing RFM for your helicopter. Furthermore, compliance with 
such

[[Page 50228]]

requirements in an AD is impracticable to demonstrate or track on an 
ongoing basis; therefore, a requirement to operate the aircraft in such 
a manner is unenforceable. Nonetheless, the FAA recommends that flight 
crews of the helicopters listed in the applicability operate in 
accordance with the revised emergency procedures mandated by this AD.

Interim Action

    The FAA considers this AD interim action. If final action is later 
identified, the FAA might consider further rulemaking then.

Costs of Compliance

    The FAA estimates that this AD affects 28 helicopters of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
New actions....................  Up to 6 work-hours x                 $0  Up to $510........  Up to $14,280.
                                  $85 per hour = $510.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    The FAA estimates that it will take about 1 work-hour per product 
to comply with the reporting requirement in this AD. The average labor 
rate is $85 per hour. Based on these figures, the FAA estimates the 
cost of reporting the inspection results on U.S. operators to be 
$2,380, or $85 per product.
    The FAA estimates the following costs to do any necessary on-
condition actions that will be required based on the results of any 
required actions. The FAA has no way of determining the number of 
helicopters that might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
40 work-hours x $85 per hour = $3,400.        $295,000         $298,400
------------------------------------------------------------------------

    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators. The FAA does not control warranty coverage for 
affected operators. As a result, the FAA has included all known costs 
in the cost estimate.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to 
Information Collection Clearance Officer, Federal Aviation 
Administration, 10101 Hillwood Pkwy., Fort Worth, TX 76177-1524.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2016-12-51, Amendment 39-18578 (81 
FR 43479, July 5, 2016); and
0
b. Adding the following new airworthiness directive:


[[Page 50229]]


2021-16-05 Airbus Helicopters: Amendment 39-21667; Docket No. FAA-
2021-0379; Project Identifier MCAI-2021-00068-R.

(a) Effective Date

    This airworthiness directive (AD) is effective October 13, 2021.

(b) Affected ADs

    This AD replaces AD 2016-12-51, Amendment 39-18578 (81 FR 43479, 
July 5, 2016) (AD 2016-12-51).

(c) Applicability

    This AD applies to all Airbus Helicopters Model AS332L2 and 
EC225LP helicopters, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6320, Main Rotor 
Gearbox.

(e) Reason

    This AD was prompted by an accident involving a Model EC225LP 
helicopter in which the main rotor hub detached from the main 
gearbox. The FAA is issuing this AD to address failure of the main 
rotor system, which would result in loss of control of the 
helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency (EASA) AD 
2017-0134R2, dated April 16, 2020 (EASA AD 2017-0134R2).

(h) Exceptions to EASA AD 2017-0134R2

    (1) Where EASA AD 2017-0134R2 refers to the effective dates 
specified in paragraphs (h)(1)(i) through (v) of this AD, this AD 
requires using the effective date of this AD.
    (i) The effective date of EASA AD 2017-0134R2.
    (ii) October 13, 2016 (the effective date of EASA AD 2016-0199, 
dated October 7, 2016).
    (iii) March 20, 2017 (the effective date of EASA AD 2017-0050-E, 
dated March 17, 2017).
    (iv) June 30, 2017 (the effective date of EASA AD 2017-0111, 
dated June 23, 2017).
    (v) August 1, 2017 (the effective date of EASA AD 2017-0134, 
dated July 27, 2017).
    (2) The ``Remarks'' section of EASA AD 2017-0134R2 does not 
apply to this AD.
    (3) Where any service information referred to in EASA AD 2017-
0134R2 specifies to discard certain parts after they have been 
removed from the helicopter, this AD requires removing those parts 
from service.
    (4) Where paragraph (2) of EASA AD 2017-0134R2 specifies to 
replace a part before exceeding the applicable ``new service life 
limit,'' this AD requires removing that part from service.
    (5) Where any service information referred to in EASA AD 2017-
0134R2 specifies to return certain parts to the manufacturer, 
including for overhaul, after they have been removed from the 
helicopter, this AD does not include that requirement.
    (6) Where EASA AD 2017-0134R2 refers to flight hours (FH), this 
AD requires using hours time-in-service.
    (7) Where any service information referred to in EASA AD 2017-
0134R2 specifies to perform a metallurgical analysis and contact the 
manufacturer if unsure about the characterization of the particles 
collected, this AD does require characterization of the particles 
collected, however this AD does not require contacting the 
manufacturer to determine the characterization of the particles 
collected.
    (8) Where EASA AD 2017-0134R2 requires actions during each 
``after last flight'' of the day (ALF) inspection, this AD requires 
those actions before the first flight of each day.
    (9) Where any service information referred to in EASA AD 2017-
0134R2 specifies to do the actions identified in paragraphs 
(h)(9)(i) through (iv) of this AD, this AD does not include those 
requirements.
    (i) Watch a video for removing the grease from the full flow 
magnetic plug (FFMP), using a cleaning agent, and collecting 
particles.
    (ii) Return affected planetary gear assembly to the manufacturer 
for module overhaul.
    (iii) Contact the approved repair station/Airbus Helicopters if 
the reason for a repair to an epicyclic module is unknown and 
inform/contact Airbus Helicopters.
    (iv) Contact the approved repair station/Airbus Helicopters 
depending on who performed the last overhaul (RG) to determine if a 
repair has been done on the second stage planet gears since new.
    (10) Where any service information referred to in EASA AD 2017-
0134R2 specifies that retrofit of the planet gear of the main 
gearbox (MGB) can only be done by Airbus Helicopters or Airbus 
Helicopters approved repair centers, this AD does not require that 
the retrofit of the planet gear be done only by Airbus Helicopters 
or Airbus Helicopters approved repair centers. For this AD the 
retrofit can also be done by an FAA-approved repair station.
    (11) Where paragraph (5) of EASA AD 2017-0134R2 specifies 
accomplishing the FFMP additional work within 3 months after August 
1, 2017, this AD requires accomplishing the FFMP additional work 
within 4 months after the effective date of this AD.
    (12) Where paragraph (6) of EASA AD 2017-0134R2 specifies to 
``inform all flight crews and, thereafter, operate the helicopter 
accordingly,'' this AD does not require those actions.
    (13) Where any service information referred to in EASA AD 2017-
0134R2 specifies that if any 16NCD13 particles are found you are to 
take a 1-liter sample of oil and send it to the manufacturer, this 
AD does not require those actions.
    (14) Where any service information referred to in EASA AD 2017-
0134R2 specifies ``Do not resume flights until corrective action(s) 
are agreed by Airbus Helicopters,'' or to contact Airbus Helicopters 
before resuming flights ``if further particles are collected during 
the close monitoring period'' for this AD, you must repair before 
further flight using a method specified in paragraph (h)(14)(i) or 
(ii) of this AD.
    (i) In accordance with FAA approved procedures.
    (ii) The procedures specified in Appendix 4.A., Particle 
Analysis, of Airbus Helicopters Emergency Alert Service Bulletin 
05A049, Revision 6, dated July 25, 2017; or Emergency Alert Service 
Bulletin 05.01.07, Revision 6, dated July 27, 2017, as applicable, 
except as required by paragraphs (h)(5), (7), and (13) of this AD.
    (15) Where the service information identified in EASA AD 2017-
0134R2 specifies to report inspection results to Airbus Helicopters, 
for this AD, report the inspection results at the applicable time 
specified in paragraph (h)(15)(i) or (ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the date of the 
inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraph (4) of EASA AD 2017-0134R2, if those actions were 
performed before the effective date of this AD using Airbus 
Helicopters Emergency Alert Service Bulletin 63.00.83 or 63A030, 
both Revision 1, both dated October 7, 2016.
    (2) Corrective action(s) for the inspections required by 
paragraphs (8) and (10) of EASA AD 2017-0134R2 accomplished on a 
helicopter before the effective date of this AD, in accordance with 
Paragraph 3.B. and Appendix 4.A. of the Accomplishment Instructions 
of the applicable Airbus Helicopters service information specified 
in paragraphs (i)(2)(i) through (viii) of this AD, as applicable, 
are acceptable to comply with the requirements of paragraph (11) of 
EASA AD 2017-0134R2 for that helicopter, but only for the corrective 
actions for the inspections required by paragraphs (8) and (10) of 
EASA AD 2017-0134R2.
    (i) Emergency Alert Service Bulletin 05.01.07, Revision 2, dated 
October 7, 2016.
    (ii) Emergency Alert Service Bulletin 05.01.07, Revision 3, 
dated February 25, 2017.
    (iii) Emergency Alert Service Bulletin 05.01.07, Revision 4, 
dated March 17, 2017.
    (iv) Emergency Alert Service Bulletin 05.01.07, Revision 5, 
dated June 23, 2017.
    (v) Emergency Alert Service Bulletin 05A049, Revision 2, dated 
October 7, 2016.
    (vi) Emergency Alert Service Bulletin 05A049, Revision 3, dated 
February 25, 2017.
    (vii) Emergency Alert Service Bulletin 05A049, Revision 4, dated 
March 17, 2017.
    (viii) Emergency Alert Service Bulletin 05A049, Revision 5, 
dated June 23, 2017.

(j) Special Flight Permit

    Special flight permits, as described in 14 CFR 21.197 and 
21.199, are prohibited.

[[Page 50230]]

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (l)(1) of 
this AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(l) Related Information

    (1) For more information about this AD, contact Mahmood Shah, 
Aviation Safety Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone 817-222-5538; email 
[email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(4) and (5) of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2017-0134R2, 
dated April 16, 2020.
    (ii) Airbus Helicopters Emergency Alert Service Bulletin 05A049, 
Revision 6, dated July 25, 2017.
    (iii) Airbus Helicopters Emergency Alert Service Bulletin 
05.01.07, Revision 6, dated July 27, 2017.
    (3) For EASA AD 2017-0134R2, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; Internet www.easa.europa.eu. You may find this 
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) For Airbus Helicopters service information, contact Airbus 
Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or 
at https://www.airbus.com/helicopters/services/technical-support.html.
    (5) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call 817-222-5110. This material may be 
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2021-0379.
    (6) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, email 
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 22, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-19247 Filed 9-7-21; 8:45 am]
BILLING CODE 4910-13-P