Airworthiness Directives; Safran Helicopter Engines, S.A. (Type Certificate Previously Held by Turbomeca S.A.) Turboshaft Engines, 49904-49907 [2021-19226]

Download as PDF 49904 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations (b) Affected ADs This AD replaces AD 2017–12–13, Amendment 39–18928 (82 FR 27983, June 20, 2017). (c) Applicability This AD applies to Airbus SAS airplanes specified in paragraphs (c)(1) through (3) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2020–0280, dated December 14, 2020 (EASA AD 2020–0280). (1) Model A318–111, –112, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –231, –232, and –233 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame, and a determination that similar cracks may develop in nearby areas of the fuselage frame and that additional airplanes are subject to the unsafe condition. The FAA is issuing this AD to address cracking of the pocket radius, which could lead to in-flight decompression of the airplane and possible injury to the passengers. (f) Compliance Comply with this AD within the compliance times specified, unless already done. lotter on DSK11XQN23PROD with RULES1 (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, EASA AD 2020–0280. (h) Exceptions to EASA AD 2020–0280 (1) Where EASA AD 2020–0280 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraph (9) of EASA AD 2020– 0280 specifies if any crack is found during any inspection to ‘‘contact Airbus for approved repair instructions and accomplish those instructions accordingly,’’ this AD requires if any cracking is found, the cracking must be repaired before further flight using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Where paragraph (10) of EASA AD 2020–0280 specifies credit for actions ‘‘in accordance with the instructions of an Airbus Repair Design Approval Sheet (RDAS), [and to] accomplish the next inspection of each repaired area in accordance with the instructions of, and within the compliance time as specified in, the applicable RDAS,’’ this AD requires using ‘‘in accordance with repair instructions approved, and within the compliance time specified in the repair approval, using a method approved by the Manager, Large Aircraft Section, VerDate Sep<11>2014 16:15 Sep 03, 2021 Jkt 253001 International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.’’ (4) Where paragraph (11) of EASA AD 2020–0280 specifies terminating actions apply only if specified ‘‘in the Airbus RDAS instructions for a repaired aeroplane,’’ this AD requires using ‘‘in repair instructions approved using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.’’ (5) The ‘‘Remarks’’ section of EASA AD 2020–0280 does not apply to this AD. (i) No Reporting Requirement Although the service information referenced in EASA AD 2020–0280 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, 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 responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (j)(2) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (k) Related Information For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223; email Sanjay.Ralhan@ faa.gov. (l) 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. (3) The following service information was approved for IBR on October 5, 2021 (86 FR 48485, August 31, 2021). (i) European Union Aviation Safety Agency (EASA) AD 2020–0280, dated December 14, 2020. (ii) [Reserved] (4) For EASA AD 2020–0280, contact 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. (5) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (6) 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/ibrlocations.html. Issued on September 1, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–19245 Filed 9–1–21; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0137; Project Identifier MCAI–2020–00269–E; Amendment 39–21688; AD 2021–17–05] RIN 2120–AA64 Airworthiness Directives; Safran Helicopter Engines, S.A. (Type Certificate Previously Held by Turbomeca S.A.) Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2014–04– 06 for all Safran Helicopter Engines, SUMMARY: E:\FR\FM\07SER1.SGM 07SER1 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations lotter on DSK11XQN23PROD with RULES1 S.A. (Safran Helicopter Engines) Arrius 2B1, 2B1A, 2B2, and 2K1 model turboshaft engines. AD 2014–04–06 required initial and repetitive inspections of the hydro-mechanical metering unit (HMU) high-pressure pump drive gear shaft splines, cleaning and inspections of the sleeve assembly splines, and replacement of the sleeve assembly on the affected high-pressure pump drive gear shaft or replacement of the HMU if the HMU fails inspection. This AD was prompted by in-flight shutdowns caused by interrupted fuel supply at the HMU. This AD requires revised inspections and continues to require cleaning of the sleeve assembly splines, and replacement of the sleeve assembly on the affected high-pressure pump drive gear shaft or replacement of the HMU if the HMU fails an inspection. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 12, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 12, 2021. ADDRESSES: For service information identified in this final rule, contact Safran Helicopter Engines, S.A., Avenue du 1er Mai, 40220 Tarnos, France; phone: +33 (0) 5 59 74 45 11. 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0137. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0137; 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, 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: Wego Wang, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7134; fax: (781) 238–7199; email: wego.wang@faa.gov. VerDate Sep<11>2014 16:15 Sep 03, 2021 Jkt 253001 SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014–04–06, Amendment 39–17764 (79 FR 9990, February 24, 2014), (AD 2014–04–06). AD 2014–04–06 applied to all Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 2K1 model turboshaft engines. The NPRM published in the Federal Register on March 12, 2021 (86 FR 14017). The NPRM was prompted by inflight shutdowns caused by interrupted fuel supply at the HMU. Since the FAA issued AD 2014–04–06, the manufacturer has published new service information that revises the inspections for certain HMUs, reduces compliance times for initial inspections, and allows application of non-cumulative tolerance of 10% of operating hours to be applied to the timing of the repetitive inspection of HMUs installed on certain engines. In the NPRM, the FAA proposed to continue to require cleaning of the sleeve assembly splines and replacing the HMU or the sleeve assembly on the affected high-pressure pump drive gear shaft if the HMU fails inspection. In the NPRM, the FAA also proposed to require initial and repetitive inspections of the HMU high-pressure pump drive gear shaft splines. The FAA is issuing this AD to address the unsafe condition on these products. The European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2020–0033, dated February 25, 2020 (referred to after this as ‘‘the MCAI’’), to address the unsafe condition on these products. The MCAI states: A number of in-flight shut-down (IFSD) occurrences have been reported for ARRIUS 2 engines. The results of the technical investigations concluded that these events were caused by deterioration of the splines on the high pressure (HP)/low pressure (LP) pump assembly drive shaft of the HMU, which eventually interrupted the fuel supply to the engine. This condition, if not detected and corrected, could lead to further cases of engine IFSD, possibly resulting in forced landing with consequent damage to the helicopter and injury to occupants. To address these occurrences, Turbome´ca published MSB 319 73 2825 (up to version G) to provide instructions for inspection of the HMU and sleeve assembly. Consequently, EASA issued AD 2013–0082 to require repetitive inspections of the drive gear shaft splines of the HP pump, and, depending on findings, accomplishment of applicable corrective action(s). Since that [EASA] AD was issued, SAFRAN published the MSB to provide specific inspection instructions for HMU PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 49905 installed on a helicopter after 31 January 2013, to reduce the compliance time for the initial inspection of Group 1 engines that were not previously inspected in accordance with version G or later of the MSB, and to provide some operational margin before the first inspection in all possible scenarios. For the reason described above, this [EASA] AD retains the requirements of AD 2013–0082, which is superseded, and requires accomplishment of the actions in accordance with the instructions of the MSB, as defined in this [EASA] AD. You may obtain further information by examining the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0137. FAA’s Determination This product has been approved by EASA and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Community, EASA has notified the agency of the unsafe condition described in the MCAI and service information. The FAA is issuing this final rule because the agency evaluated all the relevant information provided by EASA and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. Conclusion The FAA reviewed the relevant data and determined that air safety requires adoption of the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. This AD is adopted as proposed in the NPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed Safran Helicopter Engines Mandatory Service Bulletin (MSB) No. 319 73 2825, Version J, dated March 15, 2019. This MSB specifies procedures for inspecting the HMU high-pressure pump drive gear shaft splines and cleaning and inspecting the sleeve assembly splines. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES. Per Safran Helicopter Engines standing practice at the time MSB 319 73 2825, Version J, was issued, MSB 319 73 2825, Version J, is undated. The issue E:\FR\FM\07SER1.SGM 07SER1 49906 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations date for MSB 319 73 2825, Version J, appears on the Safran Helicopter Engines Arrius 2 B1 Service Bulletin Index, No. X 319 L5 980 2, dated December 11, 2020. Costs of Compliance The FAA estimates that this AD affects 194 engines installed on helicopters of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Visual inspection of drive gear shaft splines; cleaning and inspection of sleeve assembly splines. 2 work-hours × $85 per hour = $170 ............. The FAA estimates the following costs to do any necessary replacements that would be required based on the Parts cost results of the inspection. The agency has no way of determining the number of $900 Cost per product Cost on U.S. operators $1,070 $207,580 aircraft that might need these replacements: ON-CONDITION COSTS Labor cost Replace sleeve assembly on high-pressure pump drive gear shaft. Replace HMU ............................................................... 1 work-hour × $85 per hour = $85 ............................... $898 $983 1 work-hour × $85 per hour = $85 ............................... 45,000 45,085 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. (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. (a) Effective Date This airworthiness directive (AD) is effective October 12, 2021. List of Subjects in 14 CFR Part 39 (c) Applicability This AD applies to Safran Helicopter Engines, S.A. (Type Certificate previously held by Turbomeca S.A.) Arrius 2B1, 2B1A, 2B2, and 2K1 model turboshaft engines. 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: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. lotter on DSK11XQN23PROD with RULES1 Regulatory Findings The FAA has determined that 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, VerDate Sep<11>2014 16:15 Sep 03, 2021 Jkt 253001 Parts cost Cost per product Action § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive 2014–04–06, Amendment 39–17764 (79 FR 9990, February 24, 2014); and ■ b. Adding the following new airworthiness directive: ■ ■ 2021–17–05 Safran Helicopter Engines, S.A. (Type Certificate previously held by Turbomeca S.A.): Amendment 39– 21688; Docket No. FAA–2021–0137; Project Identifier MCAI–2020–00269–E. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (b) Affected ADs This AD replaces AD 2014–04–06, Amendment 39–17764 (79 FR 9990, February 24, 2014). (d) Subject Joint Aircraft System Component (JASC) Code 7320—Fuel Controlling System. (e) Unsafe Condition This AD was prompted by in-flight shutdowns caused by interrupted fuel supply at the hydro-mechanical metering unit (HMU). The FAA is issuing this AD to prevent interrupted fuel supply at the HMU. The unsafe condition, if not addressed, could result in engine in-flight shutdown, forced landing of the helicopter, damage to the helicopter and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within the compliance time specified in Table 1 to paragraph (g)(1) of this AD, as applicable, and before re-installation of the HMU after each removal from the engine, visually inspect the drive gear shaft splines of the high-pressure pump, and clean and inspect the sleeve assembly splines in accordance with paragraphs 2.4.2 and 2.4.3, or 4.4.2 and 4.4.3, as applicable, of Safran E:\FR\FM\07SER1.SGM 07SER1 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations Helicopter Engines Mandatory Service 49907 Bulletin (MSB) 319 73 2825, Version J, dated March 15, 2019. Table 1 to Paragraph (g)(l) HMU Group/ Condition Group 1 / 150 HMU operating hours or more accumulated since new or since last overhaul. Group 1 / Less than 150 HMU operating hours accumulated since new or since last overhaul. Within 500 HMU operating hours since the last inspection or since first installation of the HMU. (2) Repeat the inspection required by paragraph (g)(1) of this AD at intervals not to exceed 500 HMU operating hours since the previous inspection. Note 1 to paragraph (g)(2): A noncumulative tolerance of 10% of HMU operating hours (hrs) may be applied to the timing of each repetitive inspection, with a maximum allowable tolerance of +50 HMU operating hrs. For example, counting from the initial inspection, the repeat inspections would occur at the following times, with the tolerance noted in parentheses; 500 HMU operating hrs (+50 hrs), 1000 HMU operating hrs (+50 hrs), 1500 HMU operating hrs (+50 hrs). (3) If a rejectable indication is found during any inspection required by paragraphs (g)(1) or (2) of this AD, replace the sleeve assembly on the affected high-pressure pump drive gear shaft or replace the affected HMU in accordance with paragraph 2.4.2 or 4.4.2 of the MSB. (h) Definitions (1) A Group 1 HMU is an HMU that was first installed on or before January 31, 2013, and that has not previously been inspected in accordance with Safran Helicopter Engines MSB 319 73 2825 Version G or later. (2) A Group 2 HMU is an HMU that was first installed after January 31, 2013, or a HMU that has previously been inspected in accordance with Safran Helicopter Engines MSB 319 73 2825 Version G or later. lotter on DSK11XQN23PROD with RULES1 (i) No Reporting Requirement The reporting requirements specified in the Accomplishment Instructions, paragraph 2.4.2, of the MSB are not required by this AD. (j) Credit for Previous Actions You may take credit for any initial inspection or replacement of an HMU or the sleeve assembly on the affected high-pressure pump drive gear shaft required by paragraph (g) of this AD if you performed the inspection or replacement in accordance with Safran Helicopter Engines MSB 319 73 2825, Version G, dated January 24, 2013; Version VerDate Sep<11>2014 16:47 Sep 03, 2021 Before exceeding 200 HMU operating hours after the effective date of this AD. Jkt 253001 H, dated September 1, 2014; or Version I, dated April 26, 2016. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO 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 ECO Branch, send it to the attention of the person identified in Related Information. Information may be emailed to: ANE-AD-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. (l) Related Information For more information about this AD, contact Wego Wang, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7134; fax: fax: (781) 238–7199; email: wego.wang@faa.gov. (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 the AD specifies otherwise. (i) Safran Helicopter Engines Mandatory Service Bulletin (MSB) No. 319 73 2825, Version J, dated March 15, 2019. Note 2 to paragraph (m)(2)(i): Per Safran Helicopter Engines standing practice at the time MSB 319 73 2825, Version J, was issued, MSB 319 73 2825, Version J, is undated. The issue date for MSB 319 73 2825, Version J, appears on the Safran Helicopter Engines Arrius 2 B1 Service Bulletin Index, No. X 319 L5 980 2, dated December 11, 2020. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 (ii) [Reserved] (3) For Safran Helicopter Engines service information identified in this AD, contact Safran Helicopter Engines, S.A., Avenue du 1er Mai, 40220 Tarnos, France; phone: +33 (0) 5 59 74 45 11. (4) You may view this service information at 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. (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. Issued on August 7, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–19226 Filed 9–3–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0498; Project Identifier 2019–SW–072–AD; Amendment 39–21722; AD 2021–19–04] RIN 2120–AA64 Airworthiness Directives; He´licopte`res Guimbal Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: E:\FR\FM\07SER1.SGM 07SER1 ER07SE21.003</GPH> Group 2 Compliance Time Within 50 HMU operating hours after the effective date of this AD.

Agencies

[Federal Register Volume 86, Number 170 (Tuesday, September 7, 2021)]
[Rules and Regulations]
[Pages 49904-49907]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-19226]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0137; Project Identifier MCAI-2020-00269-E; 
Amendment 39-21688; AD 2021-17-05]
RIN 2120-AA64


Airworthiness Directives; Safran Helicopter Engines, S.A. (Type 
Certificate Previously Held by Turbomeca S.A.) Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2014-04-06 
for all Safran Helicopter Engines,

[[Page 49905]]

S.A. (Safran Helicopter Engines) Arrius 2B1, 2B1A, 2B2, and 2K1 model 
turboshaft engines. AD 2014-04-06 required initial and repetitive 
inspections of the hydro-mechanical metering unit (HMU) high-pressure 
pump drive gear shaft splines, cleaning and inspections of the sleeve 
assembly splines, and replacement of the sleeve assembly on the 
affected high-pressure pump drive gear shaft or replacement of the HMU 
if the HMU fails inspection. This AD was prompted by in-flight 
shutdowns caused by interrupted fuel supply at the HMU. This AD 
requires revised inspections and continues to require cleaning of the 
sleeve assembly splines, and replacement of the sleeve assembly on the 
affected high-pressure pump drive gear shaft or replacement of the HMU 
if the HMU fails an inspection. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective October 12, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 12, 
2021.

ADDRESSES: For service information identified in this final rule, 
contact Safran Helicopter Engines, S.A., Avenue du 1er Mai, 40220 
Tarnos, France; phone: +33 (0) 5 59 74 45 11. 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 https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0137.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0137; 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, 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: Wego Wang, Aviation Safety Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
(781) 238-7134; fax: (781) 238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2014-04-06, Amendment 39-17764 (79 FR 9990, 
February 24, 2014), (AD 2014-04-06). AD 2014-04-06 applied to all 
Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 2K1 model turboshaft engines. 
The NPRM published in the Federal Register on March 12, 2021 (86 FR 
14017). The NPRM was prompted by in-flight shutdowns caused by 
interrupted fuel supply at the HMU. Since the FAA issued AD 2014-04-06, 
the manufacturer has published new service information that revises the 
inspections for certain HMUs, reduces compliance times for initial 
inspections, and allows application of non-cumulative tolerance of 10% 
of operating hours to be applied to the timing of the repetitive 
inspection of HMUs installed on certain engines. In the NPRM, the FAA 
proposed to continue to require cleaning of the sleeve assembly splines 
and replacing the HMU or the sleeve assembly on the affected high-
pressure pump drive gear shaft if the HMU fails inspection. In the 
NPRM, the FAA also proposed to require initial and repetitive 
inspections of the HMU high-pressure pump drive gear shaft splines. The 
FAA is issuing this AD to address the unsafe condition on these 
products.
    The European Union Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
issued EASA AD 2020-0033, dated February 25, 2020 (referred to after 
this as ``the MCAI''), to address the unsafe condition on these 
products. The MCAI states:

    A number of in-flight shut-down (IFSD) occurrences have been 
reported for ARRIUS 2 engines. The results of the technical 
investigations concluded that these events were caused by 
deterioration of the splines on the high pressure (HP)/low pressure 
(LP) pump assembly drive shaft of the HMU, which eventually 
interrupted the fuel supply to the engine.
    This condition, if not detected and corrected, could lead to 
further cases of engine IFSD, possibly resulting in forced landing 
with consequent damage to the helicopter and injury to occupants.
    To address these occurrences, Turbom[eacute]ca published MSB 319 
73 2825 (up to version G) to provide instructions for inspection of 
the HMU and sleeve assembly. Consequently, EASA issued AD 2013-0082 
to require repetitive inspections of the drive gear shaft splines of 
the HP pump, and, depending on findings, accomplishment of 
applicable corrective action(s).
    Since that [EASA] AD was issued, SAFRAN published the MSB to 
provide specific inspection instructions for HMU installed on a 
helicopter after 31 January 2013, to reduce the compliance time for 
the initial inspection of Group 1 engines that were not previously 
inspected in accordance with version G or later of the MSB, and to 
provide some operational margin before the first inspection in all 
possible scenarios.
    For the reason described above, this [EASA] AD retains the 
requirements of AD 2013-0082, which is superseded, and requires 
accomplishment of the actions in accordance with the instructions of 
the MSB, as defined in this [EASA] AD.

    You may obtain further information by examining the MCAI in the AD 
docket at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2021-0137.

FAA's Determination

    This product has been approved by EASA and is approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Community, EASA has notified the agency of 
the unsafe condition described in the MCAI and service information. The 
FAA is issuing this final rule because the agency evaluated all the 
relevant information provided by EASA and determined the unsafe 
condition described previously is likely to exist or develop in other 
products of the same type design.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
requires adoption of the AD as proposed. Accordingly, the FAA is 
issuing this AD to address the unsafe condition on these products. This 
AD is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Safran Helicopter Engines Mandatory Service 
Bulletin (MSB) No. 319 73 2825, Version J, dated March 15, 2019. This 
MSB specifies procedures for inspecting the HMU high-pressure pump 
drive gear shaft splines and cleaning and inspecting the sleeve 
assembly splines. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or by the means identified in ADDRESSES.
    Per Safran Helicopter Engines standing practice at the time MSB 319 
73 2825, Version J, was issued, MSB 319 73 2825, Version J, is undated. 
The issue

[[Page 49906]]

date for MSB 319 73 2825, Version J, appears on the Safran Helicopter 
Engines Arrius 2 B1 Service Bulletin Index, No. X 319 L5 980 2, dated 
December 11, 2020.

Costs of Compliance

    The FAA estimates that this AD affects 194 engines installed on 
helicopters of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Visual inspection of drive gear shaft   2 work-hours x $85 per              $900          $1,070        $207,580
 splines; cleaning and inspection of     hour = $170.
 sleeve assembly splines.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
inspection. The agency has no way of determining the number of aircraft 
that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace sleeve assembly on high-pressure pump   1 work-hour x $85 per hour = $85            $898            $983
 drive gear shaft.
Replace HMU...................................  1 work-hour x $85 per hour = $85          45,000          45,085
----------------------------------------------------------------------------------------------------------------

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

    The FAA has determined that 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 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 2014-04-06, Amendment 39-17764 (79 
FR 9990, February 24, 2014); and
0
b. Adding the following new airworthiness directive:

2021-17-05 Safran Helicopter Engines, S.A. (Type Certificate 
previously held by Turbomeca S.A.): Amendment 39-21688; Docket No. 
FAA-2021-0137; Project Identifier MCAI-2020-00269-E.

(a) Effective Date

    This airworthiness directive (AD) is effective October 12, 2021.

(b) Affected ADs

    This AD replaces AD 2014-04-06, Amendment 39-17764 (79 FR 9990, 
February 24, 2014).

(c) Applicability

    This AD applies to Safran Helicopter Engines, S.A. (Type 
Certificate previously held by Turbomeca S.A.) Arrius 2B1, 2B1A, 
2B2, and 2K1 model turboshaft engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7320--Fuel 
Controlling System.

(e) Unsafe Condition

    This AD was prompted by in-flight shutdowns caused by 
interrupted fuel supply at the hydro-mechanical metering unit (HMU). 
The FAA is issuing this AD to prevent interrupted fuel supply at the 
HMU. The unsafe condition, if not addressed, could result in engine 
in-flight shutdown, forced landing of the helicopter, damage to the 
helicopter and injury to occupants.

(f) Compliance

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

(g) Required Actions

    (1) Within the compliance time specified in Table 1 to paragraph 
(g)(1) of this AD, as applicable, and before re-installation of the 
HMU after each removal from the engine, visually inspect the drive 
gear shaft splines of the high-pressure pump, and clean and inspect 
the sleeve assembly splines in accordance with paragraphs 2.4.2 and 
2.4.3, or 4.4.2 and 4.4.3, as applicable, of Safran

[[Page 49907]]

Helicopter Engines Mandatory Service Bulletin (MSB) 319 73 2825, 
Version J, dated March 15, 2019.
[GRAPHIC] [TIFF OMITTED] TR07SE21.003

    (2) Repeat the inspection required by paragraph (g)(1) of this 
AD at intervals not to exceed 500 HMU operating hours since the 
previous inspection.

    Note 1 to paragraph (g)(2):  A non-cumulative tolerance of 10% 
of HMU operating hours (hrs) may be applied to the timing of each 
repetitive inspection, with a maximum allowable tolerance of +50 HMU 
operating hrs. For example, counting from the initial inspection, 
the repeat inspections would occur at the following times, with the 
tolerance noted in parentheses; 500 HMU operating hrs (+50 hrs), 
1000 HMU operating hrs (+50 hrs), 1500 HMU operating hrs (+50 hrs).

    (3) If a rejectable indication is found during any inspection 
required by paragraphs (g)(1) or (2) of this AD, replace the sleeve 
assembly on the affected high-pressure pump drive gear shaft or 
replace the affected HMU in accordance with paragraph 2.4.2 or 4.4.2 
of the MSB.

(h) Definitions

    (1) A Group 1 HMU is an HMU that was first installed on or 
before January 31, 2013, and that has not previously been inspected 
in accordance with Safran Helicopter Engines MSB 319 73 2825 Version 
G or later.
    (2) A Group 2 HMU is an HMU that was first installed after 
January 31, 2013, or a HMU that has previously been inspected in 
accordance with Safran Helicopter Engines MSB 319 73 2825 Version G 
or later.

(i) No Reporting Requirement

    The reporting requirements specified in the Accomplishment 
Instructions, paragraph 2.4.2, of the MSB are not required by this 
AD.

(j) Credit for Previous Actions

    You may take credit for any initial inspection or replacement of 
an HMU or the sleeve assembly on the affected high-pressure pump 
drive gear shaft required by paragraph (g) of this AD if you 
performed the inspection or replacement in accordance with Safran 
Helicopter Engines MSB 319 73 2825, Version G, dated January 24, 
2013; Version H, dated September 1, 2014; or Version I, dated April 
26, 2016.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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 
ECO Branch, send it to the attention of the person identified in 
Related Information. 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

    For more information about this AD, contact Wego Wang, Aviation 
Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, 
MA 01803; phone: (781) 238-7134; fax: fax: (781) 238-7199; email: 
[email protected].

(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 the AD specifies otherwise.
    (i) Safran Helicopter Engines Mandatory Service Bulletin (MSB) 
No. 319 73 2825, Version J, dated March 15, 2019.

    Note 2 to paragraph (m)(2)(i):  Per Safran Helicopter Engines 
standing practice at the time MSB 319 73 2825, Version J, was 
issued, MSB 319 73 2825, Version J, is undated. The issue date for 
MSB 319 73 2825, Version J, appears on the Safran Helicopter Engines 
Arrius 2 B1 Service Bulletin Index, No. X 319 L5 980 2, dated 
December 11, 2020.

    (ii) [Reserved]
    (3) For Safran Helicopter Engines service information identified 
in this AD, contact Safran Helicopter Engines, S.A., Avenue du 1er 
Mai, 40220 Tarnos, France; phone: +33 (0) 5 59 74 45 11.
    (4) You may view this service information at 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.
    (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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on August 7, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-19226 Filed 9-3-21; 8:45 am]
BILLING CODE 4910-13-P