AD 2022-11-04

31125 Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations and intervals are allowed unless they are approved as specified in the provisions of the ‘‘Ref. Publications’’ section of EASA AD 2020–0211 or EASA AD 2021–0026. (j) New Maintenance or Inspection Program Revision Except as specified in paragraph (k) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2021–0208, dated September 15, 2021. Accomplishing the revision of the existing maintenance or inspection program required by this paragraph terminates the requirements of paragraph (g) of this AD. (k) Exceptions to EASA AD 2021–0208 (1) Where EASA AD 2021–0208 refers to its effective date, this AD requires using the effective date of this AD. (2) The requirements specified in paragraphs (1) and (2) of EASA AD 2021– 0208 do not apply to this AD. (3) Paragraph (3) of EASA AD 2021–0208 specifies to revise ‘‘the AMP’’ within 12 months after its effective date, but this AD requires revising the existing maintenance or inspection program, as applicable, within 90 days after the effective date of this AD. (4) The initial compliance time for doing the tasks specified in paragraph (3) of EASA AD 2021–0208 is at the applicable ‘‘limitations’’ as incorporated by the requirements of paragraph (3) of EASA AD 2021–0208, or within 90 days after the effective date of this AD, whichever occurs later. (5) The provisions specified in paragraphs (4) and (5) of EASA AD 2021–0208 do not apply to this AD. (6) The ‘‘Remarks’’ section of EASA AD 2021–0208 does not apply to this AD. (7) Where EASA AD 2021–0208 refers to Airbus A350 Airworthiness Limitations Section (ALS) Part 4, Revision 6 and Variation 6.1, replace the text ‘‘Airbus A350 Airworthiness Limitations Section (ALS) Part 4, Revision 6 and Variation 6.1,’’ with ‘‘Airbus A350 Airworthiness Limitations Section (ALS) Part 4, Revision 6 and Variation 6.1; for any airworthiness limitations (tasks and life limits) that are in both documents, the airworthiness limitations (tasks and life limits) specified in Variation 6.1 prevail.’’ (l) New Provisions for Alternative Actions and Intervals After the existing maintenance or inspection program has been revised as required by paragraph (j) of this AD, no alternative actions ( e.g., inspections) and intervals are allowed unless they are approved as specified in the provisions of the ‘‘Ref. Publications’’ section of EASA AD 2021–0208. (m) Terminating Action for Certain Requirements of AD 2019–20–01 Accomplishing the actions required by paragraph (g) or (j) of this AD terminates the repetitive greasing task for batch 02 group of affected thrust reverser actuators required by paragraph (g) of AD 2019–20–01. (n) Additional 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 (o) of this AD. Information may be emailed to: 9-AVS-AIR- 730-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 Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3225; email dan.rodina@faa.gov. (p) 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 June 21, 2022. (i) European Union Aviation Safety Agency (EASA) AD 2021–0208, dated September 15, 2021. (ii) [Reserved] (4) The following service information was approved for IBR on September 3, 2021 (86 FR 40934, July 30, 2021). (i) European Union Aviation Safety Agency (EASA) AD 2020–0211, dated October 5, 2020. (ii) European Union Aviation Safety Agency (EASA) AD 2021–0026, dated January 20, 2021. (5) For the EASA ADs identified in this AD, 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. (6) You may view this 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. (7) 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 fr.inspection@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibr- locations.html. Issued on April 15, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. R1–2022–10460 Filed 5–20–22; 8:45 am] BILLING CODE 0099–10–D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0146; Project Identifier AD–2021–00449–R; Amendment 39–22054; AD 2022–11–04] RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is superseding Airworthiness Directive (AD) 2020–26– 13, which applied to certain Sikorsky Aircraft Corporation (Sikorsky) Model S–92A helicopters. AD 2020–26–13 required establishing the life limit for certain part-numbered horizontal stabilizer root fittings FWD (forward root fittings) and certain part-numbered stabilizer strut fittings. AD 2020–26–13 also required repetitively inspecting certain parts, and depending on the inspection results, removing parts from service. Finally AD 2020–26–13 prohibited installing certain stabilizer assemblies on any helicopter. Since the FAA issued AD 2020–26–13, the manufacturer notified the FAA that due to an error in the service information, certain part numbers in AD 2020–26–13 are incorrect. Also, the FAA determined that additional inspections are required to address the unsafe condition. This AD retains certain requirements and the prohibition for installing certain stabilizer assemblies on any helicopter from AD 2020–26–13, corrects certain part numbers, and requires additional repetitive inspections. The actions of this AD are intended to address an unsafe condition on these products. DATES : This AD is effective June 27, 2022. VerDate Sep<11>2014 16:26 May 20, 2022 Jkt 256001 PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1 lotter on DSK11XQN23PROD with RULES1

31126 Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 1, 2021 (85 FR 84201, December 28, 2020). ADDRESSES : For service information identified in this final rule, contact Sikorsky’s Engineering Group at Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbell, CT 06611, United States; phone: (800) 946–4337; email: wcs _ cust _ service _ eng.gr-sik@ lmco.com; website: www.sikorsky360.com. 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. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA–2022–0146. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov in Docket No. FAA–2022–0146; 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, any service information that is incorporated by reference, 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 : Dorie Resnik, Aerospace Engineer, Aviation Safety Section, Boston ACO Branch, Compliance & Airworthiness Division, 1200 District Avenue, Burlington, MA 01803; telephone (781) 238–7693; email 9-AVS-AIR-BACO- COS@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2020–26–13, Amendment 39–21368 (85 FR 84201, December 28, 2020) (AD 2020–26–13). AD 2020–26–13 applied to Sikorsky Model S–92A helicopters with forward root fitting part number (P/N) 92209– 07111–101 or 92070–20125–101; or stabilizer strut fitting P/N 92209–07404– 041, 92209–07403–041, or 92070– 20117–041 installed on horizontal stabilizer assembly (stabilizer assembly) P/N 92070–20117–045, 92070–20117– 046, 92070–20125–041, 92070–20125– 042, 92070–20125–043, 92070–20125– 044, 92205–07400–043, or 92205– 07400–045. The NPRM published in the Federal Register on February 23, 2022 (87 FR 10115). The NPRM was prompted by the discovery that incorrect P/Ns were identified in the Applicability and the Required Actions paragraphs of AD 2020–26–13. Additionally, after the FAA issued AD 2020–26–13, Sikorsky notified the FAA that an additional repetitive inspection of certain parts of the stabilizer strut assembly is required to prevent the unsafe condition. Finally, after the FAA issued AD 2020–26–13, Sikorsky requested and the FAA approved a global Alternative Method of Compliance (AMOC) to allow only removing parts from service that are cracked, corroded, or have fretting, deformation, or wear rather than require removing the upper and lower support strut rod ends, including lug and conical fitting and both upper and lower attachment fittings on the stabilizer from service. In the NPRM, the FAA proposed to expand the applicability of AD 2020– 26–13 by adding an additional part- numbered stabilizer assembly. The NPRM also proposed to correct paragraph (g)(4) of the Required Actions so that the installation of the titanium stabilizer strut fitting is terminating action for the 50-hour time-in-service (TIS) inspections of the aluminum stabilizer strut fitting. The NPRM also proposed to require an additional repetitive inspection of certain parts of the stabilizer strut assembly. Finally, the NPRM proposed to incorporate the FAA approved global AMOC. Discussion of Final Airworthiness Directive Comments The FAA received a comments from Sikorsky stating that in the section titled ‘‘Actions Since AD 2020–26–13 Was Issued’’ of the NPRM, the part number specified (92070–20117–04) is incorrect and should be 92070–20117–041. The FAA acknowledges this comment; however, the part number is not used in the ‘‘Background’’ section of this final rule. In light of this, the commenter’s request no longer applies. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 This AD continues to require S–92 Maintenance Manual, SA S92A–AMM– 000, Temporary Revision (TR) 55–33, dated March 24, 2020 (TR 55–33), which the Director of the Federal Register approved for incorporation by reference as of February 1, 2021 (85 FR 84201, December 28, 2020). 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 the ADDRESSES section. Other Related Service Information The FAA reviewed S–92 Maintenance Manual SA S92A–AWL–000, TR No. 4– 58, dated October 2, 2017 (TR 4–58), and S–92 Maintenance Manual SA S92A–AWL–000, TR No. 4–66 dated November 20, 2019 (TR 4–66). This service information revises Task 4–00– 00–200–000, Table 1 Replacement Schedule, dated November 30, 2015. Both TR 4–58 and 4–66 revise the Airworthiness Limitations Schedule by removing certain part-numbered components, introducing new part- numbered components, and establishing replacement intervals and recurring inspections for the forward root fitting and the horizontal stabilizer strut fitting. TR 4–58 also specifies inspecting the horizontal stabilizer and attaching hardware at a recurring interval of 250 hours TIS. Differences Between This AD and the Service Information The service information requires returning affected parts to a Sikorsky specialist; this AD does not. Costs of Compliance The FAA estimates that this AD affects 82 helicopters of U.S. registry. Labor costs are estimated at $85 per work-hour. Based on these numbers, the FAA estimates the following costs to comply with this AD. Visually inspecting the stabilizer assembly and attached hardware takes about 3 work-hours for an estimated cost of $255 per helicopter and $20,910 for the U.S. fleet per inspection cycle. If required, replacing a hat bushing and both upper fittings and lower fittings takes about 1 work-hour and parts cost about $10,000 for an estimated cost of $10,085 per replacement. VerDate Sep<11>2014 16:26 May 20, 2022 Jkt 256001 PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1 lotter on DSK11XQN23PROD with RULES1

31127 Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations If required, replacing the upper and lower support strut rod ends, including lug and conical fitting, takes about 1 work-hour and parts cost about $10,000 for an estimated cost of $10,085 per replacement. If required, replacing Mylar washers takes about 0.5 work-hour and parts cost about $76 for an estimated cost of $119 per replacement. If required, performing a fluorescent penetrant inspection takes about 3 work-hours for an estimated cost of $255 per inspection. If required, replacing a stabilizer assembly takes about 6 work-hours and parts cost about $312,000 for an estimated cost of $312,510 per replacement. If required, replacing a forward root fitting takes about 10 work-hours and parts cost about $25,000 for an estimated cost of $25,850 per replacement. If required, replacing a stabilizer strut fitting takes about 10 work-hours and parts cost about $10,000 for an estimated cost of $10,850 per replacement. If required, replacing a forward root fitting and an aft attachment fitting takes about 20 work-hours and parts cost about $50,000 for an estimated cost of $51,700 per replacement. If required, removing wear or corrosion and applying corrosion preventative compound takes about 0.5 work-hour and parts cost a nominal amount for an estimated cost of $43 per action. If required, replacing a stabilizer attachment bolt and barrel nut set takes about 1 work-hour and parts cost about $500 for an estimated cost of $585 per replacement. If required, replacing a fastener takes about 0.1 work-hour and parts cost a nominal amount for an estimated cost of $9 per fastener. If required, removing the abrasion- resistant Teflon coating to inspect each forward and aft attachment fitting mating surface takes about 5 work-hours for an estimated cost of $425 per inspection. If required, applying alodine or equivalent and applying abrasion- resistant Teflon coating takes about 5 work hours with minimal parts cost for an estimated cost of $425 per application. According to Sikorsky, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all costs in this cost estimate. 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 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 ■ 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: ■ a. Removing Airworthiness Directive AD 2020–26–13, Amendment 39–21368 (85 FR 84201, December 28, 2020); and ■ b. Adding the following new airworthiness directive: 2022–11–04 Sikorsky Aircraft Corporation: Amendment 39–22054; Docket No. FAA–2022–0146; Project Identifier AD– 2021–00449–R. (a) Effective Date This airworthiness directive (AD) is effective June 27, 2022. (b) Affected ADs This AD replaces AD 2020–26–13, Amendment 39–21368 (85 FR 84201, December 28, 2020) (AD 2020–26–13). (c) Applicability This AD applies to Sikorsky Aircraft Corporation Model S–92A helicopters, certificated in any category, with the following installed: Horizontal stabilizer root fitting FWD (forward root fitting) part number (P/N) 92209–07111–101 or 92070– 20125–101; or stabilizer strut fitting P/N 92209–07403–041 or 92070–20117–041 installed on horizontal stabilizer assembly (stabilizer assembly) P/N 92070–20117–045, 92070–20117–046, 92070–20125–041, 92070–20125–042, 92070–20125–043, 92070–20125–044, 92205–07400–043, 92205–07400–045, or 92205–07400–047. (d) Subject Joint Aircraft System Component (JASC) Code: 5510, Horizontal Stabilizer Structure. (e) Unsafe Condition This AD was prompted by incidents of fatigue cracks in a forward root fitting and life limit recalculations for forward root fitting P/N 92209–07111–101 and 92070– 20125–101. The FAA is issuing this AD to prevent a forward root fitting from remaining in service beyond its life limit, detect fatigue cracking in a forward root fitting, and prevent increased load and stress cracking in the stabilizer root fitting aft. The unsafe condition, if not addressed, could result in failure of a stabilizer root fitting, separation of the stabilizer assembly from the helicopter, and subsequent loss of control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 50 hours time-in-service (TIS) after the effective date of this AD: (i) Determine the total hours TIS of the forward root fitting P/N 92209–07111–101 or 92070–20125–101. If the total hours TIS of the forward root fitting is unknown, use the total hours TIS of the stabilizer assembly instead. (A) If the forward root fitting has accumulated 7,900 or more total hours TIS, before further flight, remove the forward root fitting from service. (B) If the forward root fitting has accumulated less than 7,900 total hours TIS, VerDate Sep<11>2014 16:26 May 20, 2022 Jkt 256001 PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1 lotter on DSK11XQN23PROD with RULES1

31128 Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations before exceeding 7,900 total hours TIS, remove the forward root fitting from service. (ii) Thereafter following paragraph (g)(1)(i) of this AD, remove the forward root fitting from service before accumulating 7,900 total hours TIS. (iii) For stabilizer assemblies with stabilizer strut fitting P/N 92070–20117–041 installed, perform the following actions: (A) Determine the total hours TIS of stabilizer strut fitting P/N 92070–20117–041. (B) If the stabilizer strut fitting has accumulated 19,100 or more total hours TIS, before further flight, remove the stabilizer strut fitting from service. (C) If the stabilizer strut fitting has accumulated less than 19,100 total hours TIS, before exceeding 19,100 total hours TIS, remove the stabilizer strut fitting from service. (iv) Thereafter following paragraph (g)(1)(iii) of this AD, remove the stabilizer strut fitting from service before accumulating 19,100 total hours TIS. (2) For helicopters with stabilizer strut fitting P/N 92070–20117–041 or 92209– 07403–041 installed, within 50 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 50 hours TIS: (i) Remove the support strut and using a cheese cloth (or similar cloth) and isopropyl alcohol, clean the upper and lower support strut rod ends, horizontal stabilizer attachment fitting, and the tail rotor pylon attachment fitting. (ii) If installed, visually inspect the surface of each Mylar washer P/N 92070–20117–104 (Mylar washer). The surface should be smooth and continuous. If there is any visible damage such as any tear or scrape, remove the Mylar washer from the peelable-ply washer P/N 92070–20117–105 (peelable-ply washer) and remove the Mylar washer from service as follows: (A) Dampen a low-lint cloth with 3M 6041 adhesive remover and place on the top of the Mylar washer. (B) Allow the adhesive remover to soften the Mylar washer and peel the Mylar washer back. (C) Repeat with more solvent until the Mylar washer and adhesive are removed. (D) Clean the peelable-ply washer with cheese cloth moistened with isopropyl alcohol and adhere a new Mylar washer to the peelable-ply washer. Note 1 to paragraph (g)(2)(ii): Stabilizer assembly P/Ns 92070–20125–041, 92070– 20125–042, 92070–20125–043, and 92070– 20125–044 do not utilize the Mylar washer. The inspection of the Mylar washer is not required on helicopters with stabilizer assembly P/N 92070–20125–041, 92070– 20125–042, 92070–20125–043, or 92070– 20125–044 installed. (iii) Using a 10X or higher power magnifying glass, a flashlight, and a mirror, visually inspect the hat bushing and both upper fittings and lower fittings for a crack, corrosion, fretting, deformation, and wear. If there is a crack, corrosion, fretting, deformation, or wear on any part, before further flight, remove the part from service. (iv) Using a 10X or higher power magnifying glass, a flashlight, and a mirror, visually inspect both upper and lower support strut rod ends, including each lug and conical fitting, and both upper and lower attachment fittings on the stabilizer and pylon including the bushings for a crack, corrosion, fretting, deformation, and wear. If there is a crack, corrosion, fretting, deformation, or wear on any part, before further flight, remove the part from service. (3) Within 250 hours TIS or one year, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 250 hours TIS or one year, whichever occurs first: (i) Remove the stabilizer assembly and visually inspect each stabilizer attachment bolt and barrel nut set for corrosion, a crack, and damage to the threads. For the purposes of this inspection, damage may be indicated by uneven threads, missing threads, or cross- threading. (A) If there is corrosion within allowable limits, before further flight, treat for corrosion in accordance with FAA-approved procedures. (B) If there is corrosion that exceeds allowable limits, or a crack, or damage to the threads, before further flight, remove the bolt and barrel nut set from service. (ii) Inspect the forward root fitting and the aft attachment fitting by: (A) Gaining access to the inside of the horizontal stabilizer. (B) Using Brulin Cleaner SD 1291 (or equivalent) and a low-lint cloth, remove all traces of sealing compound, oil, and dirt from the stabilizer mounting surfaces. (C) Using a 10X or higher magnifying glass, inspect for any crack, wear, and corrosion. ( 1 ) If there is a crack, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( 2 ) If there is wear or corrosion that exceeds allowable limits, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( 3 ) If there is wear or corrosion within allowable limits, before further flight, treat for corrosion in accordance with FAA- approved procedures. (D) Visually inspect each attachment fitting bolt hole and fastener hole for a crack, wear, and corrosion. ( 1 ) If there is a crack, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( 2 ) If there is wear or corrosion that exceeds allowable limits, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( 3 ) If there is wear or corrosion within allowable limits, before further flight, treat for corrosion in accordance with FAA approved procedures. (E) Inspect for loose or working fasteners. If there is a loose or working fastener, before further flight, remove the fastener from service. (iii) As an alternative means to inspect for cracks in paragraphs (g)(3)(i) and (ii) of this AD, perform a florescent penetrant inspection (FPI). (iv) Visually inspect each forward and aft attachment fitting mating surface for wear of the abrasion-resistant Teflon coating and degradation. For the purposes of this inspection, degradation may be indicated by fretting. Refer to Figure 204, of S–92 Maintenance Manual, SA S92A–AMM–000, Temporary Revision 55–33, Task 55–11–01– 210–004, dated March 24, 2020 (TR 55–33), for a depiction of the area to be inspected. For the purposes of this inspection, wear may be indicated by less than 100% coverage of the abrasion-resistant Teflon coating. If there is wear to the abrasion-resistant Teflon coating or degradation, before further flight: (A) Chemically strip the abrasion-resistant Teflon coating from the entire mounting pad in accordance with paragraph 7.A.(7)(a) of TR 55–33. (B) FPI or eddy current inspect for a crack. If there is a crack, before further flight, remove the stabilizer assembly from service. (C) If there is no crack, treat the affected area by applying alodine or equivalent. Apply abrasion-resistant Teflon coating in accordance with paragraphs 7.A.(7)(d) through (e) of TR 55–33. (4) Installing stabilizer strut fitting P/N 92209–07404–041 is a terminating action for the requirements in paragraph (g)(2) of this AD. (5) As of the effective date of this AD, do not install stabilizer assembly P/N 92205– 07400–043, 92205–07400–045, or 92205– 07400–047 on any helicopter. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston ACO 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 certification office, send it to the attention of the person identified in paragraph (i) of this AD. (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 For more information about this AD, contact Dorie Resnik, Aerospace Engineer, Boston ACO Branch, 1200 District Avenue, Burlington, Massachusetts 01803; telephone 781–238–7693; email 9-AVS-AIR-BACO- COS@faa.gov. (j) 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. (3) The following service information was approved for IBR on February 1, 2021 (85 FR 84201, December 28, 2020). VerDate Sep<11>2014 16:26 May 20, 2022 Jkt 256001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1 lotter on DSK11XQN23PROD with RULES1

31129 Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations (i) S–92 Maintenance Manual, SA S92A– AMM–000, Temporary Revision (TR) 55–33, dated March 24, 2020. (ii) [Reserved] (4) For Sikorsky Aircraft Corporation service information identified in this AD, contact Sikorsky’s Engineering Group at Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbell, CT 06611, United States; phone: (800) 946–4337; email: wcs _ cust _ service _ eng.gr-sik@lmco.com; website: www.sikorsky360.com. (5) You may view this service information at 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: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on May 16, 2022. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–10952 Filed 5–20–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0518; Project Identifier MCAI–2021–00822–T; Amendment 39–22046; AD 2022–10–08] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320–214, –251N, and –271N airplanes. This AD was prompted by reports that damaged seat rail covers were detected in the forward and aft seat fixation area of some airplanes during initial delivery. This AD requires a one-time detailed inspection of the affected passenger seats and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA). The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD becomes effective June 7, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 7, 2022. The FAA must receive comments on this AD by July 7, 2022. ADDRESSES : You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For material incorporated by reference (IBR) in this AD, 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 IBR material on the EASA website at https://ad.easa.europa.eu. You may view this 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 at https://www.regulations.gov by searching for and locating Docket No. FAA–2022–0518. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2022–0518; 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 street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT : Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229; email vladimir.ulyanov@faa.gov. SUPPLEMENTARY INFORMATION : Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES . Include ‘‘Docket No. FAA–2022–0518; Project Identifier MCAI–2021–00822–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this final rule. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229; email vladimir.ulyanov@ faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2021–0166, dated July 13, 2021 (EASA AD 2021– 0166) (also referred to as the MCAI), to correct an unsafe condition for certain Airbus SAS Model A320–214, –251N, and –271N airplanes. This AD was prompted by reports that damaged seat rail covers were detected in the forward and aft seat fixation area of some airplanes during initial delivery. The FAA is issuing this AD to VerDate Sep<11>2014 16:26 May 20, 2022 Jkt 256001 PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1 lotter on DSK11XQN23PROD with RULES1