AD 2022-13-15

39738 Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations 2022–13–13 Airbus SAS: Amendment 39– 22099; Docket No. FAA–2022–0382; Project Identifier MCAI–2021–01452–T. (a) Effective Date This airworthiness directive (AD) is effective August 9, 2022. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model A350–941 and –1041 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Unsafe Condition This AD was prompted by reports that passenger door stop screws were found with missing screw heads. The FAA is issuing this AD to address the missing door stop screw heads, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2021–0291, dated December 22, 2021 (EASA AD 2021–0291). (h) Exceptions to EASA AD 2021–0291 (1) Where EASA AD 2021–0291 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2021–0291 does not apply to this AD. (3) Paragraph (4) of EASA AD 2021–0291 specifies to report results of the initial inspection to Airbus within a certain compliance time. For this AD, report inspection results of the initial inspection at the applicable time specified in paragraph (h)(3)(i) or (ii) of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the end of the maintenance visit/check during which the inspection was performed. (ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the end of the maintenance visit/check during which the inspection was performed or within 30 days after the effective date of this AD, whichever occurs later. (4) Where Note 2 of paragraph (2) of EASA AD 2021–0291 specifies using ‘‘the instructions from an applicable Airbus Repair Design Approval Form (RDAF)’’ is acceptable for compliance with the corrective actions, this AD requires using corrective actions 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) Where paragraph (2) of EASA AD 2021– 0291 refers to passenger door stop screws that are ‘‘damaged, as defined in the SB’’ this AD defines damage as broken passenger door stop screws. (6) Where service information referenced in EASA AD 2021–0291 specifies ‘‘a general visual inspection of the adjacent door stop area and surrounding structure (no lining removal required),’’ for this AD do a general visual inspection for any damage ( e.g., broken passenger door stop screws), and repair any damage 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. (i) Return of Parts Although the service information referenced in EASA AD 2021–0291 specifies to send broken screws to Airbus, this AD does not include that requirement. (j) Special Flight Permit Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the airplane to a location where the actions of this AD can be performed (if the operator elects to do so), provided no passengers are onboard. (k) 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 (l) 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. (3) Required for Compliance (RC): Except as required by paragraph (k)(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. (l) Related Information For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone and fax 206–231–3225; email dan.rodina@ 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 this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2021–0291, dated December 22, 2021. (ii) [Reserved] (3) For EASA AD 2021–0291, 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 material on the EASA website at https:// ad.easa.europa.eu. (4) 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. (5) 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 June 15, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–14195 Filed 7–1–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0511; Project Identifier AD–2020–01229–E; Amendment 39–22101; AD 2022–13–15] RIN 2120–AA64 Airworthiness Directives; Williams International Co., L.L.C. Turbofan Engines AGENCY : Federal Aviation Administration (FAA), DOT. VerDate Sep<11>2014 15:56 Jul 01, 2022 Jkt 256001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1 lotter on DSK11XQN23PROD with RULES1

39739 Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Williams International Co., L.L.C. (Williams) FJ44–2A, FJ44–2C, FJ44–3A, and FJ44–3A–24 model turbofan engines. This AD was prompted by a report of cracks in the high-pressure turbine (HPT) disk posts and failure of an HPT disk post, resulting in the contained fracture of an HPT disk post and blade. This AD requires removing the HPT disk, part number (P/N) 67093, from service before reaching defined cycle limits and replacing it with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective August 9, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 9, 2022. ADDRESSES : For service information identified in this final rule, contact Williams International, Product Support, 2000 Centerpoint Parkway, Pontiac, MI 48341; phone: (800) 859– 3544; website: http://www.williams- int.com/product-support. 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 (817) 222– 5110. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0511; 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 : Kyle Bush, Aviation Safety Engineer, Chicago ACO, FAA, 2300 East Devon Avenue, Des Plaines, IL 60018; phone: (847) 294– 7870; email: kyle.bush@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Williams FJ44–2A, FJ44–2C, FJ44–3A, and FJ44–3A–24 model turbofan engines. The SNPRM published in the Federal Register on April 14, 2022 (87 FR 22153). The SNPRM was prompted by a report of cracks in the HPT disk posts and failure of an HPT disk post, resulting in the contained fracture of an HPT disk post and blade. Subsequently, Williams notified the FAA that revised service information was available, which added additional serial- numbered FJ44–2A, FJ44–2C, and FJ44– 3A model turbofan engines to the effectivity and updated the compliance time for replacing the HPT disk. In the SNPRM, the FAA proposed to require removing the HPT disk, P/N 67093, from service before reaching defined cycle limits and replacing it with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the SNPRM or on the determination of the costs. Conclusion The FAA reviewed the relevant data and determined that air safety requires adopting this 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 SNPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed Williams International Service Bulletin (SB) WISB–72–1032, Revision 2, dated June 4, 2020. This SB specifies procedures for removing and replacing the HPT rotor assemblies that include HPT disk, P/N 67093. This SB also provides instructions for incorporating the latest HPT combustor/fuel slinger module on FJ44–2A and FJ44–2C model turbofan engines. 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 . Other Related Service Information The FAA reviewed Williams International SB WISB–72–1034, Revision 3, dated July 2, 2021. This SB describes procedures for re-identifying the HPT rotor assembly and HPT disk. Costs of Compliance The FAA estimates that this AD affects 242 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Remove and replace the HPT disk ................ 33 work-hours × $85 per hour = $2,805 ........ $16,694 $19,499 $4,718,758 The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. 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. VerDate Sep<11>2014 15:56 Jul 01, 2022 Jkt 256001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1 lotter on DSK11XQN23PROD with RULES1

39740 Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations 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 ■ 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: 2022–13–15 Williams International Co., L.L.C.: Amendment 39–22101; Docket No. FAA–2021–0511; Project Identifier AD–2020–01229–E. (a) Effective Date This airworthiness directive (AD) is effective August 9, 2022. (b) Affected ADs None. (c) Applicability This AD applies to Williams International Co., L.L.C. (Williams) FJ44–2A, FJ44–2C, FJ44–3A, and FJ44–3A–24 model turbofan engines with an engine serial number identified in paragraph 1.A., Effectivity, of Williams International Service Bulletin WISB–72–1032, Revision 2, dated June 4, 2020 (the SB), with an installed high- pressure turbine (HPT) disk, part number (P/ N) 67093. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a report of cracks in the HPT disk posts and failure of an HPT disk post, resulting in the contained fracture of an HPT disk post and blade. The FAA is issuing this AD to prevent cracking and failure of the HPT disk posts. The unsafe condition, if not addressed, could result in release of the HPT blade, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For FJ44–2A and FJ44–2C model turbofan engines, within the compliance times specified in Table 1 to Paragraph (g) of this AD, remove the affected HPT disk from service and replace it with a part eligible for installation using paragraphs 2.C. and E., Accomplishment Instructions—FJ44–2A & FJ44–2C, of the SB. (2) For FJ44–3A and FJ44–3A–24 model turbofan engines, within the compliance times specified in Table 1 to Paragraph (g) of this AD, remove the affected HPT disk from service and replace it with a part eligible for installation using paragraphs 3.C. and D., of the SB. (h) Installation Prohibition After the effective date of this AD, do not install onto any engine an HPT disk with P/ N 67093. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Chicago ACO, 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 (j) 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. (j) Related Information For more information about this AD, contact Kyle Bush, Aviation Safety Engineer, Chicago ACO, FAA, 2300 East Devon Avenue, Des Plaines, IL 60018; phone: (847) 294–7870; email: kyle.bush@faa.gov . (k) 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) Williams International Service Bulletin WISB–72–1032, Revision 2, dated June 4, 2020. (ii) [Reserved] (3) For service information identified in this AD, contact Williams International, Product Support, 2000 Centerpoint Parkway, Pontiac, MI 48341; phone: (800) 859–3544; website: http://www.williams-int.com/ product-support. (4) You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, FAA, 1200 District Avenue, Burlington, MA 01803. For VerDate Sep<11>2014 15:56 Jul 01, 2022 Jkt 256001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1 ER05JY22.000</GPH> lotter on DSK11XQN23PROD with RULES1 Table 1 to Paragraph (g) - Compliance Time HPT disk, PIN 67093, cycles since new (CSN) as of the effective date of this AD 0 to 999 CSN 1,000 to 1,999 CSN 2,000 to 2,999 CSN 3,000 or higher CSN Replace within HPT disk cycles after the effective date of this AD 620 530 245 130

39741 Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on June 17, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–14183 Filed 7–1–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0464; Project Identifier MCAI–2021–01290–T; Amendment 39–22097; AD 2022–13–11] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350–941 and –1041 airplanes. This AD was prompted by a report of inadvertent auto flight system (AFS) altitude changes on the flight control unit (FCU). This AD requires revising the existing airplane flight manual (AFM) to include a procedure on the use of the AFS control panel ALT knob and replacing any affected FCU with a serviceable FCU, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective August 9, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 9, 2022. ADDRESSES : 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–2022–0464. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2022–0464; 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 : Dan Rodina, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225; email dan.rodina@faa.gov. SUPPLEMENTARY INFORMATION : Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2021–0260, dated November 18, 2021 (EASA AD 2021–0260) (also referred to as the MCAI), to correct an unsafe condition for all Airbus SAS Model A350–941 and –1041 airplanes. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus SAS Model A350– 941 and –1041 airplanes. The NPRM published in the Federal Register on April 18, 2022 (87 FR 22816). The NPRM was prompted by a report of inadvertent AFS altitude changes on the FCU. The NPRM proposed to require revising the existing AFM to include a procedure on the use of the AFS control panel ALT knob and replacing any affected FCU with a serviceable FCU, as specified in EASA AD 2021–0260. The NPRM also proposed to prohibit the installation of affected parts. The FAA is issuing this AD to address erroneous target altitude during descent, climb, or go-around, which could result in an unexpected vertical trajectory deviation and loss of correct situational awareness that could potentially result in uncontrolled impact with the ground. See the MCAI for additional background information. Discussion of Final Airworthiness Directive Comments The FAA received a comment from the Air Line Pilots Association, International (ALPA) who supported the NPRM without change. Conclusion The FAA reviewed the relevant data, considered the comment received, and determined that air safety requires adopting this AD as proposed. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Related Service Information Under 1 CFR part 51 EASA AD 2021–0260 describes procedures for revising the existing AFM to include a procedure on the use of the AFS control panel ALT knob and replacing any affected FCU having part numbers (P/N) C31006AC01 or C31006AB01 with a serviceable FCU having P/N C31006AD01. 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. Costs of Compliance The FAA estimates that this AD affects 27 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS FOR R EQUIRED A CTIONS Labor cost Parts cost Cost per product Cost on U.S. operators Up to 6 work-hours × $85 per hour = $510 ..................................................................... $27,000 Up to $27,510 ..... Up to $742,770. VerDate Sep<11>2014 15:56 Jul 01, 2022 Jkt 256001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1 lotter on DSK11XQN23PROD with RULES1