Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France), 38220-38223 [2021-15302]

Download as PDF 38220 Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations (a) Effective Date This airworthiness directive (AD) is effective August 24, 2021. (b) Affected ADs This AD replaces AD 2011–18–52, Amendment 39–17020 (77 FR 23109, April 18, 2012) (AD 2011–18–52). (c) Applicability This AD applies to Leonardo S.p.a. (type certificate previously held by Agusta S.p.A.) Model AB139 and AW139 helicopters, certificated in any category, with tail rotor (T/R) blade, part number (P/N) 3G6410A00131, 3G6410A00132, 3G6410A00133, 4G6410A00131, 4G6410A00132, or 4G6410A00133, installed. (d) Subject Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor Blades. (e) Unsafe Condition This AD defines the unsafe condition as a crack in a T/R blade. This condition could result in failure of a T/R blade and subsequent loss of control of the helicopter. khammond on DSKJM1Z7X2PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For T/R blade P/Ns 3G6410A00131 and 4G6410A00131, within 5 hours time-inservice (TIS) after May 3, 2012 (the effective date of AD 2011–18–52), establish a life limit of 600 hours TIS or 1,500 takeoff and landing cycles (cycles), whichever occurs first, on the affected T/R blades and update the helicopter’s historical records. If a T/R blade’s total number of cycles is unknown, determine the T/R blade cycles by multiplying the T/R blade’s hours TIS by 4. (2) For T/R blade P/Ns 3G6410A00131 and 4G6410A00131, thereafter following paragraph (g)(1) of this AD, remove any T/R blade from service before accumulating 600 total hours TIS or 1,500 total cycles, whichever occurs first. (3) For T/R blade P/Ns 3G6410A00132, 3G6410A00133, 4G6410A00132, and 4G6410A00133, within 5 hours TIS after the effective date of this AD, determine the total number of cycles. If a T/R blade’s total number of cycles is unknown, determine the T/R blade cycles by multiplying the blade’s hours TIS by 4. Before further flight, remove any T/R blade from service that has accumulated or exceeded its life limit as follows. Thereafter, remove any T/R blade from service before accumulating its life limit as follows: (i) T/R blade P/Ns 3G6410A00132 and 4G6410A00132: 1,200 total hours TIS or 3,200 total cycles, whichever occurs first. (ii) T/R blade P/N 3G6410A00133: 40,000 total cycles. (iii) T/R blade P/N 4G6410A00133: 4,033 total hours TIS or 40,000 cycles, whichever occurs first. Note 1 to paragraph (g)(3): A combination of T/R blades having different P/Ns can be installed on the same helicopter. The eligible combinations of T/R blades P/N are listed in VerDate Sep<11>2014 15:59 Jul 19, 2021 Jkt 253001 AgustaWestland Mandatory Bollettino Tecnico No. 139–265, Revision B, dated February 18, 2014 (BT No. 139–265). (4) For T/R blade P/Ns 3G6410A00131 and P/N 4G6410A00131, within 25 hours TIS after the effective date of this AD, and thereafter at intervals not to exceed 25 hours TIS, visually inspect the T/R blade for a crack and damage that exceeds allowable limits. Inspect in the area depicted in Figure 1 of BT No. 139–265 using a mirror, a 5X or higher power magnifying glass, and a flashlight, or borescope. If there is a crack or damage that exceeds allowable limits, before further flight, remove the T/R blade from service. (5) As of the effective date of this AD, do not install on any helicopter any T/R blade P/N 3G6410A00131 or P/N 4G6410A00131, unless the actions required by paragraphs (g)(1), (2), and (4) of this AD have been accomplished. (h) 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 (i)(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. (i) Related Information (1) For more information about this AD, contact Matt Fuller, AD Program Manager, General Aviation & Rotorcraft Unit, Airworthiness Products Section, Operational Safety Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222– 5110; email matthew.fuller@faa.gov. (2) The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2012–0076R2, dated February 20, 2014. You may view the EASA AD at https:// www.regulations.gov in Docket No. FAA– 2021–0348. (j) 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) AgustaWestland Mandatory Bollettino Tecnico No. 139–265, Revision B, dated February 18, 2014. (ii) [Reserved] (3) For service information identified in this AD, contact Leonardo S.p.A. Helicopters, Emanuele Bufano, Head of Airworthiness, Viale G.Agusta 520, 21017 C. Costa di Samarate (Va) Italy; telephone +39–0331– PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 225074; fax +39–0331–229046; or at https:// www.leonardocompany.com/en/home. (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: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on July 2, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–15303 Filed 7–19–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0175; Project Identifier 2001–SW–33–AD; Amendment 39– 21643; AD 2021–14–16] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters (type certificate previously held by Eurocopter France) Model SA–365N, SA–365N1, AS– 365N2, AS 365 N3, and SA–366G1 helicopters. This AD was prompted by a quality control check that revealed some stretcher attachment holes were improperly located on the frame where there was insufficient edge distance. This AD requires measuring the 9degree frame flange (frame) for the correct edge distance of the four attachment holes for the stretcher support and inspecting for cracks, and repairing the frame, if necessary, and installation of a reinforcement plate (reinforcing angle), as specified in two Direction Ge´ne´rale de l’Aviation Civile (DGAC) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 24, 2021. SUMMARY: E:\FR\FM\20JYR1.SGM 20JYR1 Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 24, 2021. ADDRESSES: For DGAC material incorporated by reference (IBR) in this AD, contact the European Union Aviation Safety Agency (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 the DGAC material on the EASA website at https://ad.easa.europa.eu. For American Eurocopter material, contact Airbus Helicopters, 2701 N 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 the DGAC and American Eurocopter material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. Service information that is incorporated by reference is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0175. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0175; 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 DGAC ADs, any comments received, and other information. The street 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: Blaine Williams, Aerospace Engineer, Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 90712; telephone 562–627–5371; email blaine.williams@faa.gov. SUPPLEMENTARY INFORMATION: khammond on DSKJM1Z7X2PROD with RULES Background The DGAC, which was the Technical Agent for France, issued DGAC AD 2001–061–053(A), dated February 21, VerDate Sep<11>2014 15:59 Jul 19, 2021 Jkt 253001 2001 (DGAC AD 2001–061–053(A)) for certain Model SA–365N, SA–365N1, AS–365N2, and AS 365 N3 helicopters; and DGAC AD 2001–283–025(A), dated July 11, 2001 (DGAC AD 2001–283– 025(A)) for all Model SA–366G1 helicopters (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for those helicopters. The FAA issued a second supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Helicopters (type certificate previously held by Eurocopter France) Model SA–365N, SA–365N1, AS–365N2, AS 365 N3, and SA–366G1 helicopters. The second SNPRM published in the Federal Register on May 7, 2021 (86 FR 24556). The second SNPRM proposed to require inspecting the frame for the correct edge distance of the four attachment holes of the stretcher support and for a crack, and repairing the frame, if necessary, and installation of a reinforcement plate (reinforcing angle) on the frame, as specified in DGAC AD 2001–061– 053(A) and DGAC AD 2001–283– 025(A). The second SNPRM also included references to an engineering report that lists approved U.S. alternative fasteners and materials that may be used in any required repairs. The second SNPRM was issued because a significant amount of time elapsed since the first SNPRM was published. The FAA is issuing this AD to address failure of the 9-degree frame due to a crack at the stretcher support attachment holes, which could result in loss of a passenger door, damage to the rotor system, and subsequent loss of control of the helicopter. See the MCAI for additional background information. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the second SNPRM or on the determination of the costs. 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: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 38221 • Are consistent with the intent that was proposed in the second SNPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the second SNPRM. Related Service Information Under 1 CFR Part 51 DGAC AD 2001–061–053(A) and DGAC AD 2001–283–025(A) describe procedures for measuring the edge distance of the webs at the four attachment holes of the stretcher support on the left and right sides of the 9-degree frame, and additional actions depending on the findings. The additional actions include repetitively inspecting the frame for cracking, repair if necessary, and installation of a reinforcement plate (reinforcing angle) on the frame. These documents are distinct since they refer to different helicopter models. American Eurocopter Engineering Report No. AEC/03R–E–005, ‘‘Addendum ASB 53.00.42 and 53.00.43 AS365,’’ dated January 29, 2003, specifies U.S. and European rivet equivalent part numbers, U.S. rivet part numbers with acceptable substitute materials with greater strength properties, and 5 rivet, 6 rivet, and pin Hi-lok alternatives. 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 The FAA has determined that acceptable U.S. alternatives to the fasteners and materials needed to perform repairs or modifications are listed in American Eurocopter Engineering Report No. AEC/03R–E–005 ‘‘Addendum ASB 53.00.42 and 53.00.043 AS365’’, dated January 29, 2003. Where DGAC AD 2001–061–053(A) exempts helicopters that were delivered after January 31, 2001, from the applicability, this AD does not exempt those helicopters. Costs of Compliance The FAA estimates that this AD affects 31 helicopters of U.S. registry. The FAA estimates the following costs to comply with this AD: E:\FR\FM\20JYR1.SGM 20JYR1 38222 Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 3 work-hours × $85 per hour = $255 .......................................................................................... $100 $355 $11,005 The FAA estimates the following costs to do any necessary on-condition actions that would 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 ACTION Labor cost Parts cost Cost per product Up to 8 work-hours × $85 per hour = $680 ............................................................................................................ $250 Up to $930 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 helicopters identified in this rulemaking action. khammond on DSKJM1Z7X2PROD with RULES 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. VerDate Sep<11>2014 15:59 Jul 19, 2021 Jkt 253001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–14–16 Airbus Helicopters (Type Certificate Previously Held by Eurocopter France): Amendment 39– 21643; Docket No. FAA–2021–0175; Project Identifier 2001–SW–33–AD. (a) Effective Date This airworthiness directive (AD) is effective August 24, 2021. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters (type certificate previously held by Eurocopter France) Model SA–365N, SA– 365N1, AS–365N2, AS 365 N3, and SA– 366G1 helicopters, certificated in any category. (d) Subject Joint Aircraft Service Component (JASC) Code 5311, Fuselage Main, Frame. (e) Reason This AD was prompted by a quality control check that revealed some stretcher attachment holes were improperly located on the frame where there was insufficient edge PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 distance. The FAA is issuing this AD to address failure of the 9-degree frame flange (frame) due to a crack at the stretcher support attachment holes, which could result in loss of a passenger door, damage to the rotor system, and subsequent 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 the applicable Direction Ge´ne´rale de l’Aviation Civile (DGAC) ADs specified in paragraphs (g)(1) and (2) of this AD. (1) For Model SA–365N, SA–365N1, AS– 365N2, and AS 365 N3 helicopters: DGAC AD 2001–061–053(A), dated February 21, 2001, (DGAC AD 2001–061–053(A)). (2) For Model SA–366G1 helicopters: DGAC AD 2001–283–025(A), dated July 11, 2001 (DGAC AD 2001–283–025(A)). (h) Exceptions to DGAC AD 2001–061– 053(A) and DGAC AD 2001–283–025(A) (1) Where paragraph 3.1 of DGAC AD 2001–061–053(A) and DGAC AD 2001–283– 025(A) specifies an initial compliance time to do the measurement, for this AD, do the measurement within 50 hours time-in-service (TIS) after the effective date of this AD. (2) Where paragraph 3.1. of DGAC AD 2001–061–053(A) and DGAC AD 2001–283– 025(A) specifies to do a measurement, for this AD, do an inspection of the area around the attachment holes for cracks concurrently with the measurement. (3) Where paragraph 3.2.1.a) of DGAC AD 2001–061–053(A) and DGAC AD 2001–283– 025(A) specifies ‘‘every 550 flight hours, check that there is no crack in the flange,’’ for this AD, inspect (check) the area around the attachment holes for cracks at intervals not to exceed 550 hours TIS. (4) Where paragraph 3.2.1.b) of DGAC AD 2001–061–053(A) and DGAC AD 2001–283– 025(A) requires installation of a reinforcement plate (reinforcing angle) on the flange for certain helicopters, do the E:\FR\FM\20JYR1.SGM 20JYR1 Federal Register / Vol. 86, No. 136 / Tuesday, July 20, 2021 / Rules and Regulations installation within 550 hours TIS after accomplishment of the measurement specified in paragraph 3.1. of DGAC AD 2001–061–053(A) and DGAC AD 2001–283– 025(A). (5) Where the service information referred to in DGAC AD 2001–061–053(A) and DGAC AD 2001–283–025(A) specifies to perform a dye penetrant crack inspection ‘‘if in doubt,’’ this AD requires performing a dye penetrant inspection. (6) Where paragraph 3.2.2. of DGAC AD 2001–061–053(A) and DGAC AD 2001–283– 025(A) specifies to do various actions specified in paragraphs 3.2.2.a), b), and c) of those ADs, for this AD, if any frame is cracked, before further flight, repair the frame. Acceptable U.S. alternatives to the fasteners and materials needed to perform repairs or modifications are listed in American Eurocopter Engineering Report No. AEC/03R–E–005, ‘‘Addendum ASB 53.00.42 and 53.00.43 AS365’’, dated January 29, 2003. (7) Where the Note in paragraph 3.2.2. of DGAC AD 2001–061–053(A) and DGAC AD 2001–283–025(A) specifies the instructions are no longer applicable after a customized repair has been carried out, for this AD, modifying or repairing the frame constitutes terminating action for the requirements of this AD. (i) Special Flight Permit Special flight permits, as described in 14 CFR 21.197 and 21.199, are prohibited. (j) 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 (k) 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. khammond on DSKJM1Z7X2PROD with RULES (k) Related Information For more information about this AD, contact Blaine Williams, Aerospace Engineer, Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 90712; telephone 562–627–5371; email blaine.williams@faa.gov. (l) 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. VerDate Sep<11>2014 15:59 Jul 19, 2021 Jkt 253001 (i) Direction Ge´ne´rale de l’Aviation Civile (DGAC) AD 2001–061–053(A), dated February 21, 2001. (ii) DGAC AD 2001–283–025(A), dated July 11, 2001. (iii) American Eurocopter Engineering Report No. AEC/03R–E–005, ‘‘Addendum ASB 53.00.42 and 53.00.43 AS365’’, dated January 29, 2003. (3) For DGAC AD 2001–061–053(A) and DGAC AD 2001–283–025(A), contact the European Union Aviation Safety Agency (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 these DGAC ADs on the EASA website at https:// ad.easa.europa.eu. (4) For American Eurocopter material identified in this AD, contact Airbus Helicopters, 2701 N 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. (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: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on July 2, 2021. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–15302 Filed 7–19–21; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0031; Project Identifier MCAI–2020–01420–T; Amendment 39–21625; AD 2021–13–20] RIN 2120–AA64 Airworthiness Directives; Airbus Canada Limited Partnership (Type Certificate Previously Held by C Series Aircraft Limited Partnership (CSALP); Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership SUMMARY: Frm 00015 Fmt 4700 Model BD–500–1A10 and BD–500– 1A11 airplanes. This AD was prompted by reports of corrosion on the waste box, waste access doubler, and waste service door of the rear fuselage due to contamination from waste valve leakage. This AD requires an inspection for corrosion of the waste box, waste access doubler, and waste service door, and corrective actions if necessary, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. This AD is effective August 24, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 24, 2021. DATES: For material incorporated by reference (IBR) in this AD, contact TCCA, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario, K1A 0N5, Canada; telephone 888–663–3639; email AD-CN@tc.gc.ca; internet https:// tc.canada.ca/en/aviation. You may view this IBR material 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. 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– 0031. ADDRESSES: Examining the AD Docket BILLING CODE 4910–13–P PO 00000 38223 Sfmt 4700 You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0031; 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: Siddeeq Bacchus, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7362; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: E:\FR\FM\20JYR1.SGM 20JYR1

Agencies

[Federal Register Volume 86, Number 136 (Tuesday, July 20, 2021)]
[Rules and Regulations]
[Pages 38220-38223]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-15302]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0175; Project Identifier 2001-SW-33-AD; Amendment 
39-21643; AD 2021-14-16]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Helicopters (type certificate previously held by Eurocopter 
France) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 
helicopters. This AD was prompted by a quality control check that 
revealed some stretcher attachment holes were improperly located on the 
frame where there was insufficient edge distance. This AD requires 
measuring the 9-degree frame flange (frame) for the correct edge 
distance of the four attachment holes for the stretcher support and 
inspecting for cracks, and repairing the frame, if necessary, and 
installation of a reinforcement plate (reinforcing angle), as specified 
in two Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) 
ADs, which are incorporated by reference. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective August 24, 2021.

[[Page 38221]]

    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 24, 
2021.

ADDRESSES: For DGAC material incorporated by reference (IBR) in this 
AD, contact the European Union Aviation Safety Agency (EASA), Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; 
email [email protected]; internet www.easa.europa.eu. You may find the 
DGAC material on the EASA website at https://ad.easa.europa.eu. For 
American Eurocopter material, contact Airbus Helicopters, 2701 N 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 the DGAC and American Eurocopter 
material at the FAA, Office of the Regional Counsel, Southwest Region, 
10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. Service 
information that is incorporated by reference is also available at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-0175.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0175; 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 
DGAC ADs, any comments received, and other information. The street 
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: Blaine Williams, Aerospace Engineer, 
Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, 
Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 
90712; telephone 562-627-5371; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The DGAC, which was the Technical Agent for France, issued DGAC AD 
2001-061-053(A), dated February 21, 2001 (DGAC AD 2001-061-053(A)) for 
certain Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters; 
and DGAC AD 2001-283-025(A), dated July 11, 2001 (DGAC AD 2001-283-
025(A)) for all Model SA-366G1 helicopters (also referred to as the 
Mandatory Continuing Airworthiness Information, or the MCAI), to 
correct an unsafe condition for those helicopters.
    The FAA issued a second supplemental notice of proposed rulemaking 
(SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all 
Airbus Helicopters (type certificate previously held by Eurocopter 
France) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 
helicopters. The second SNPRM published in the Federal Register on May 
7, 2021 (86 FR 24556). The second SNPRM proposed to require inspecting 
the frame for the correct edge distance of the four attachment holes of 
the stretcher support and for a crack, and repairing the frame, if 
necessary, and installation of a reinforcement plate (reinforcing 
angle) on the frame, as specified in DGAC AD 2001-061-053(A) and DGAC 
AD 2001-283-025(A). The second SNPRM also included references to an 
engineering report that lists approved U.S. alternative fasteners and 
materials that may be used in any required repairs. The second SNPRM 
was issued because a significant amount of time elapsed since the first 
SNPRM was published.
    The FAA is issuing this AD to address failure of the 9-degree frame 
due to a crack at the stretcher support attachment holes, which could 
result in loss of a passenger door, damage to the rotor system, and 
subsequent loss of control of the helicopter. See the MCAI for 
additional background information.

Discussion of Final Airworthiness Directive

Comments

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

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 
second SNPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the second SNPRM.

Related Service Information Under 1 CFR Part 51

    DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) describe 
procedures for measuring the edge distance of the webs at the four 
attachment holes of the stretcher support on the left and right sides 
of the 9-degree frame, and additional actions depending on the 
findings. The additional actions include repetitively inspecting the 
frame for cracking, repair if necessary, and installation of a 
reinforcement plate (reinforcing angle) on the frame. These documents 
are distinct since they refer to different helicopter models.
    American Eurocopter Engineering Report No. AEC/03R-E-005, 
``Addendum ASB 53.00.42 and 53.00.43 AS365,'' dated January 29, 2003, 
specifies U.S. and European rivet equivalent part numbers, U.S. rivet 
part numbers with acceptable substitute materials with greater strength 
properties, and 5 rivet, 6 rivet, and pin Hi-lok alternatives.
    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

    The FAA has determined that acceptable U.S. alternatives to the 
fasteners and materials needed to perform repairs or modifications are 
listed in American Eurocopter Engineering Report No. AEC/03R-E-005 
``Addendum ASB 53.00.42 and 53.00.043 AS365'', dated January 29, 2003.
    Where DGAC AD 2001-061-053(A) exempts helicopters that were 
delivered after January 31, 2001, from the applicability, this AD does 
not exempt those helicopters.

Costs of Compliance

    The FAA estimates that this AD affects 31 helicopters of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 38222]]



                                      Estimated Costs For Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255...........................            $100             $355          $11,005
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions that would 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 Action
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
Up to 8 work-hours x $85 per hour =               $250       Up to $930
 $680.................................
------------------------------------------------------------------------

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 helicopters 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 adding the following new airworthiness 
directive:

2021-14-16 Airbus Helicopters (Type Certificate Previously Held by 
Eurocopter France): Amendment 39-21643; Docket No. FAA-2021-0175; 
Project Identifier 2001-SW-33-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective August 24, 2021.

 (b) Affected ADs

    None.

 (c) Applicability

    This AD applies to all Airbus Helicopters (type certificate 
previously held by Eurocopter France) Model SA-365N, SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 helicopters, certificated in any 
category.

 (d) Subject

    Joint Aircraft Service Component (JASC) Code 5311, Fuselage 
Main, Frame.

 (e) Reason

    This AD was prompted by a quality control check that revealed 
some stretcher attachment holes were improperly located on the frame 
where there was insufficient edge distance. The FAA is issuing this 
AD to address failure of the 9-degree frame flange (frame) due to a 
crack at the stretcher support attachment holes, which could result 
in loss of a passenger door, damage to the rotor system, and 
subsequent 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 the applicable Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC) ADs specified in paragraphs (g)(1) and (2) 
of this AD.
    (1) For Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 
helicopters: DGAC AD 2001-061-053(A), dated February 21, 2001, (DGAC 
AD 2001-061-053(A)).
    (2) For Model SA-366G1 helicopters: DGAC AD 2001-283-025(A), 
dated July 11, 2001 (DGAC AD 2001-283-025(A)).

 (h) Exceptions to DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A)

    (1) Where paragraph 3.1 of DGAC AD 2001-061-053(A) and DGAC AD 
2001-283-025(A) specifies an initial compliance time to do the 
measurement, for this AD, do the measurement within 50 hours time-
in-service (TIS) after the effective date of this AD.
    (2) Where paragraph 3.1. of DGAC AD 2001-061-053(A) and DGAC AD 
2001-283-025(A) specifies to do a measurement, for this AD, do an 
inspection of the area around the attachment holes for cracks 
concurrently with the measurement.
    (3) Where paragraph 3.2.1.a) of DGAC AD 2001-061-053(A) and DGAC 
AD 2001-283-025(A) specifies ``every 550 flight hours, check that 
there is no crack in the flange,'' for this AD, inspect (check) the 
area around the attachment holes for cracks at intervals not to 
exceed 550 hours TIS.
    (4) Where paragraph 3.2.1.b) of DGAC AD 2001-061-053(A) and DGAC 
AD 2001-283-025(A) requires installation of a reinforcement plate 
(reinforcing angle) on the flange for certain helicopters, do the

[[Page 38223]]

installation within 550 hours TIS after accomplishment of the 
measurement specified in paragraph 3.1. of DGAC AD 2001-061-053(A) 
and DGAC AD 2001-283-025(A).
    (5) Where the service information referred to in DGAC AD 2001-
061-053(A) and DGAC AD 2001-283-025(A) specifies to perform a dye 
penetrant crack inspection ``if in doubt,'' this AD requires 
performing a dye penetrant inspection.
    (6) Where paragraph 3.2.2. of DGAC AD 2001-061-053(A) and DGAC 
AD 2001-283-025(A) specifies to do various actions specified in 
paragraphs 3.2.2.a), b), and c) of those ADs, for this AD, if any 
frame is cracked, before further flight, repair the frame. 
Acceptable U.S. alternatives to the fasteners and materials needed 
to perform repairs or modifications are listed in American 
Eurocopter Engineering Report No. AEC/03R-E-005, ``Addendum ASB 
53.00.42 and 53.00.43 AS365'', dated January 29, 2003.
    (7) Where the Note in paragraph 3.2.2. of DGAC AD 2001-061-
053(A) and DGAC AD 2001-283-025(A) specifies the instructions are no 
longer applicable after a customized repair has been carried out, 
for this AD, modifying or repairing the frame constitutes 
terminating action for the requirements of this AD.

(i) Special Flight Permit

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

(j) 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 (k) 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.

(k) Related Information

    For more information about this AD, contact Blaine Williams, 
Aerospace Engineer, Cabin Safety & Environmental Systems Section, 
Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 
Paramount Blvd., Lakewood, CA 90712; telephone 562-627-5371; email 
[email protected].

(l) 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) Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) 
AD 2001-061-053(A), dated February 21, 2001.
    (ii) DGAC AD 2001-283-025(A), dated July 11, 2001.
    (iii) American Eurocopter Engineering Report No. AEC/03R-E-005, 
``Addendum ASB 53.00.42 and 53.00.43 AS365'', dated January 29, 
2003.
    (3) For DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A), 
contact the European Union Aviation Safety Agency (EASA), Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; 
email [email protected]; internet www.easa.europa.eu. You may find 
these DGAC ADs on the EASA website at https://ad.easa.europa.eu.
    (4) For American Eurocopter material identified in this AD, 
contact Airbus Helicopters, 2701 N 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.
    (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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 2, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-15302 Filed 7-19-21; 8:45 am]
BILLING CODE 4910-13-P