Airworthiness Directives; International Aero Engines AG Turbofan Engines, 13225-13228 [2021-04236]

Download as PDF Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules the existing maintenance manual or ICA for your airplane as follows: (i) Replace the ALS with the Airworthiness Limitations Section of Pilatus PC–6 Airworthiness Limitations Document No. 02334, Revision 10, dated October 30, 2020. (ii) Add (or replace, if applicable) Appendix K, Fuselage Wing Fittings— Inspection/Check, of Pilatus PC 6 Airworthiness Limitations Document No. 02334, Revision 10, dated October 30, 2020. (iii) Add Appendix L, Wing to Fuselage Fittings—Inspection/Check, of Pilatus PC 6 Airworthiness Limitations Document No. 02334, Revision 9, dated March 6, 2020. (3) For all airplanes specified in paragraph (c) of this AD, after revising the ALS as required by paragraphs (f)(1) and (2) of this AD, remove from service each part that has reached or exceeded its new life limit. (g) Inspections and Replacement (1) For airplanes with a bush part number (P/N) 6100.0020.01 that has been bonded as specified in Section 53–00–01, Fuselage Wing Fittings—Inspection/Check, of Pilatus PC–6 Aircraft Maintenance Manual Document No. 01975, Revision 29, dated February 28, 2020; or Appendix K, Fuselage Wing Fittings—Inspection/Check, of Pilatus PC–6 Airworthiness Limitations Document No. 02334, Revision 9, dated March 6, 2020: Within 50 hours time-in-service (TIS) after the effective date of this AD, perform a visual and eddy current inspection of each fuselage wing fitting on fuselage Frame 3, remove bush P/N 6100.0020.01 from service, and install a new (zero hours TIS) bush P/N 6100.0020.01 into Frame 3 with grease by using the procedures specified in paragraph (f)(1)(ii) or (f)(2)(ii) of this AD, as applicable to your airplane. (2) Unless already done, within 1,100 hours TIS after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, perform an eddy current inspection of each fuselage wing fitting and each wing-to-fuselage fitting using the procedures specified in paragraphs (f)(1)(ii) and (iii) of this AD, or paragraphs (f)(2)(ii) and (iii) of this AD, as applicable to your airplane. Thereafter, repeat the eddy current inspection of each fuselage wing fitting and each wing-to-fuselage fitting at the intervals specified in the ALS identified in paragraph (f)(1)(i) or (f)(2)(i), as applicable to your airplane. jbell on DSKJLSW7X2PROD with PROPOSALS (h) No Alternative Actions or Intervals After the ALS has been revised as required by paragraph (f) of this AD, no alternative inspection intervals or procedures may be approved, except as provided in paragraph (i) of this AD. (i) Other FAA AD Provisions Alternative Methods of Compliance (AMOCs): 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. Send your request to the person identified in Related Information. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspection, the manager of the local Flight Standards District Office. VerDate Sep<11>2014 16:28 Mar 05, 2021 Jkt 253001 (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Union Aviation Safety Agency (EASA) AD No. 2020–0120, dated May 27, 2020, and EASA AD No. 2020–0278, dated December 14, 2020, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2020–0857. (2) For more information about this AD, contact Doug Rudolph, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, MO 64106; telephone: (816) 329–4059; fax: (816) 329– 4090; email: doug.rudolph@faa.gov. (3) For service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Support General Aviation, CH– 6371 Stans, Switzerland; telephone: +41 848 24 7 365; email: Techsupport@ pilatusaircraft.com; internet: https:// www.pilatusaircraft.com/en. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued on February 25, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–04395 Filed 3–5–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2021–0129; Project Identifier AD–2020–01597–E] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, V2531–E5, and V2533–A5 model turbofan engines. This proposed AD was prompted by an analysis performed by the manufacturer after an event involving an uncontained failure of a high-pressure turbine (HPT) 1st-stage disk that resulted in highenergy debris penetrating the engine cowling. This proposed AD would require the performance of an ultrasonic SUMMARY: Frm 00009 Fmt 4702 inspection (USI) of the HPT 1st-stage disk and HPT 2nd-stage disk and, depending on the results of the inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by April 7, 2021. 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 service information identified in this NPRM, contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06118; phone: (800) 565– 0140; email: help24@pw.utc.com; website: http://fleetcare.pw.utc.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238–7759. Examining the AD Docket 14 CFR Part 39 PO 00000 13225 Sfmt 4702 You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0129; 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 NPRM, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Nicholas Paine, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7742; fax: (781) 238– 7199; email: nicholas.j.paine@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–0129; Project Identifier AD– 2020–01597–E’’ at the beginning of your comments. The most helpful comments E:\FR\FM\08MRP1.SGM 08MRP1 13226 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules reference a specific portion of the proposal, 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 proposal because of those comments. The FAA has been informed that IAE has done some outreach with affected operators regarding the proposed corrective actions for this unsafe condition. As a result, affected operators are already aware of the proposed corrective actions and, in some cases, have already begun planning for implementation. Therefore, the FAA has determined that a 30-day comment period is appropriate given the particular circumstances related to the proposed correction of this unsafe condition. 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 NPRM. 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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to Nicholas Paine, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background On March 18, 2020, an Airbus Model A321–231 airplane, powered by IAE V2533–A5 model turbofan engines, experienced an uncontained HPT 1ststage disk failure that resulted in an aborted takeoff. The uncontained failure of the HPT 1st-stage disk resulted in high-energy debris penetrating the engine cowling. The FAA published Emergency AD 2020–07–51 on March 21, 2020 (followed by publication in the Federal Register on April 13, 2020, as a Final Rule, Request for Comments (85 FR 20402)) and AD 2021–01–03 on January 6, 2021 (86 FR 458), to remove from service HPT 1st-stage and HPT 2nd-stage disks identified as having the highest risk of failure. Based on the root cause analysis performed since that event, the manufacturer identified a population of HPT 1st-stage disks and HPT 2nd-stage disks that require inspection and possible removal from service. This condition, if not addressed, could result in uncontained HPT disk failure, damage to the engine, damage to the airplane, and loss of the airplane. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed IAE NonModification Service Bulletin (NMSB) No. V2500–ENG–72–0713, Revision 1, dated January 26, 2021. The NMSB identifies the affected HPT 1st-stage disks and HPT 2nd-stage disks on IAE V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines and specifies procedures for a USI of the HPT 1ststage disk and HPT 2nd-stage disk. The FAA also reviewed IAE NMSB No. V2500–E5–72–0015, dated December 15, 2020. The NMSB identifies the affected HPT 1st-stage disks and HPT 2nd-stage disks on IAE V2531–E5 model turbofan engines and specifies procedures for a USI of the HPT 1st-stage disk and HPT 2nd-stage disk. 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. Proposed AD Requirements in This NPRM This proposed AD would require the performance of a USI of the HPT 1ststage disk and HPT 2nd-stage disk and, depending on the results of the inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk with a part eligible for installation. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 1,100 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: jbell on DSKJLSW7X2PROD with PROPOSALS ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators USI the HPT 1st-stage disk and HPT 2ndstage disk. 20 work-hours × $85 per hour = $1,700 ........ $0 $1,700 $1,870,000 The FAA estimates the following costs to do any necessary replacement that would be required based on the VerDate Sep<11>2014 17:32 Mar 05, 2021 Jkt 253001 results of the proposed inspections. The agency has no way of determining the PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 number of aircraft that might need this replacement: E:\FR\FM\08MRP1.SGM 08MRP1 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 13227 ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Replace the HPT 1st-stage disk or HPT 2nd-stage disk. 0 work-hours × $85 per hour = $0 ............................... $300,000 $300,000 The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this proposed 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. jbell on DSKJLSW7X2PROD with PROPOSALS Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would 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. VerDate Sep<11>2014 17:32 Mar 05, 2021 Jkt 253001 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: ■ International Aero Engines AG: Docket No. FAA–2021–0129; Project Identifier AD– 2020–01597–E. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by April 7, 2021. (b) Affected ADs None. (c) Applicability This AD applies to International Aero Engines AG (IAE) V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, V2531– E5, and V2533–A5 model turbofan engines with an installed: (1) High-pressure turbine (HPT) 1st-stage disk, part number (P/N) 2A5001, with a serial number (S/N) listed in Appendix A, Table 1, of IAE Non-Modification Service Bulletin (NMSB) No. V2500–ENG–72–0713, Revision 1, dated January 26, 2021 (IAE NMSB V2500– ENG–72–0713, Revision 1) or IAE NMSB No. V2500–E5–72–0015, dated December 15, 2020 (IAE NMSB V2500–E5–72–0015); and/ or (2) HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–ENG–72–0713, Revision 1, or IAE NMSB V2500–E5–72–0015. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by an analysis performed by the manufacturer after an event involving an uncontained failure of a HPT 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. The FAA is issuing this AD to prevent failure of the HPT 1st-stage disk and HPT 2nd-stage disk. The unsafe condition, if not addressed, could result in uncontained HPT disk failure, PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 damage to the engine, damage to the airplane, and loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For IAE V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500–ENG–72– 0713, Revision 1, at the next engine shop visit after the effective date of this AD or before the HPT 1st-stage disk has accumulated 3,200 flight cycles (FCs) since the effective date of this AD, whichever occurs first, perform an ultrasonic inspection (USI) of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500–ENG–72–0713, Revision 1. (2) For IAE V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–ENG–72– 0713, Revision 1, at the next engine shop visit after the effective date of this AD or before the HPT 2nd-stage disk has accumulated 3,200 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500–ENG–72– 0713, Revision 1. (3) For IAE V2522–A5, V2524–A5, V2525– D5, and V2527–A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500–ENG–72–0713, Revision 1, at the next HPT rotor and stator assembly (HPT module) removal or before the HPT 1st-stage disk has accumulated 6,700 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500–ENG–72–0713, Revision 1. (4) For IAE V2522–A5, V2524–A5, V2525– D5, and V2527–A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–ENG–72–0713, Revision 1, at the next HPT module removal or before the HPT 2nd-stage disk has accumulated 6,700 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500–ENG–72– 0713, Revision 1. (5) For IAE V2531–E5 model turbofan engines with an HPT 1st-stage disk, P/N E:\FR\FM\08MRP1.SGM 08MRP1 13228 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500–E5–72–0015, at the next engine shop visit or before the HPT 1st-stage disk has accumulated 3,200 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 1ststage disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB V2500–E5–72–0015. (6) For IAE V2531–E5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500–E5–72–0015, at the next engine shop visit or before the HPT 2nd-stage disk has accumulated 3,200 FCs since the effective date of this AD, whichever occurs first, perform a USI of the HPT 2ndstage disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB V2500–E5–72–0015. (7) If, during the USI required by paragraphs (g)(1) through (6) of this AD, a HPT 1st-stage disk or HPT 2nd-stage disk does not pass the inspection as specified in the Accomplishment Instructions, paragraph 8., of IAE NMSB V2500–ENG–72–0713, Revision 1, or IAE NMSB V2500–E5–72– 0015, as applicable, before further flight, remove the HPT 1st-stage disk or 2nd-stage disk, as applicable, from service and replace with a part eligible for installation. AG, 400 Main Street, East Hartford, CT 06118; phone: (800) 565–0140; email: help24@pw.utc.com; website: http:// fleetcare.pw.utc.com. You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238–7759. (h) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, H–P, except for the following situations, which do not constitute an engine shop visit. (1) Separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance. (2) Engine removal for the purpose of performing field maintenance activities at a maintenance facility in lieu of performing them on-wing. Airworthiness Directives; Eurocopter France Helicopters jbell on DSKJLSW7X2PROD with PROPOSALS (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in Related Information. You may email your request to: ANE-AD-AMOC@ faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (j) Related Information (1) For more information about this AD, contact Nicholas Paine, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7742; fax: (781) 238–7199; email: nicholas.j.paine@faa.gov. (2) For service information identified in this AD, contact International Aero Engines VerDate Sep<11>2014 16:28 Mar 05, 2021 Jkt 253001 Issued on February 24, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–04236 Filed 3–5–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27495; Project Identifier 2005–SW–14–AD] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Proposed rule; withdrawal. AGENCY: The FAA is withdrawing a notice of proposed rulemaking (NPRM) that proposed to adopt a new airworthiness directive (AD) that would have applied to certain Eurocopter France (now Airbus Helicopters) Model AS350B, BA, B1, B2, B3, C, D, and D1; EC–130B4; and AS355E, F, F1, F2, and N helicopters. The NPRM would have required modifying the collective holddown strap (strap) and thereafter inspecting it at specified intervals to ensure the rubber grommet is resting against the console or replacing the strap with a strap that has a torsional spring at the lower end of the strap. Since issuance of the NPRM, the FAA issued AD 2014–02–05, which addresses the unsafe condition identified in the NPRM. Accordingly, the NPRM is withdrawn. DATES: As of March 8, 2021, the proposed rule, which was published in the Federal Register on March 13, 2007 (72 FR 11297), is withdrawn. ADDRESSES: SUMMARY: Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2007– 27495; or in person at Docket Operations between 9 a.m. and 5 p.m., PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Monday through Friday, except Federal holidays. The AD docket contains this AD action, 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: Vince Massey, Aerospace Engineer, Systems and Equipment Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3545; email: vince.massey@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued an NPRM that proposed to amend 14 CFR part 39 by adding an AD that would have applied to the specified products. The NPRM was published in the Federal Register on March 13, 2007 (72 FR 11297). The NPRM was prompted by reports of two accidents occurring while the pilots were performing an autorotation. The pilots were unable to arrest the descent of the helicopter using collective blade pitch due to the collective stick locking in the down position when the collective was lowered during the maneuver. The NPRM proposed to require modifying the strap and thereafter inspecting it at specified intervals to ensure the rubber grommet is resting against the console or replacing the strap with a strap that has a torsional spring at the lower end of the strap. Actions Since the NPRM Was Issued Since issuance of the NPRM, the FAA has published AD 2014–02–05, Amendment 39–17733 (79 FR 5251, January 31, 2014) (AD 2014–02–05), which addresses the unsafe condition for Model AS350B, BA, B1, B2, B3, C, D, and D1 helicopters identified in the NPRM. The FAA also determined that the Model EC–130B4 helicopters and Model AS355E, F, F1, F2, and N helicopters identified in the NPRM are not affected by the unsafe condition because the root cause of the unsafe condition is certain collective straps that are only installed on the Model AS350B, BA, B1, B2, B3, C, D, and D1 helicopters. Therefore, the FAA has determined that this AD action is not appropriate. AD 2014–02–05 includes certain helicopters that were not included in the NPRM. Although the NPRM applied only to helicopters with a certain partnumbered hold-down strap, AD 2014– 02–05 applies to Model AS350B, BA, E:\FR\FM\08MRP1.SGM 08MRP1

Agencies

[Federal Register Volume 86, Number 43 (Monday, March 8, 2021)]
[Proposed Rules]
[Pages 13225-13228]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-04236]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0129; Project Identifier AD-2020-01597-E]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, 
V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, 
and V2533-A5 model turbofan engines. This proposed AD was prompted by 
an analysis performed by the manufacturer after an event involving an 
uncontained failure of a high-pressure turbine (HPT) 1st-stage disk 
that resulted in high-energy debris penetrating the engine cowling. 
This proposed AD would require the performance of an ultrasonic 
inspection (USI) of the HPT 1st-stage disk and HPT 2nd-stage disk and, 
depending on the results of the inspections, replacement of the HPT 
1st-stage disk or HPT 2nd-stage disk. The FAA is proposing this AD to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by April 7, 
2021.

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 service information identified in this NPRM, contact 
International Aero Engines AG, 400 Main Street, East Hartford, CT 
06118; phone: (800) 565-0140; email: [email protected]; website: http://fleetcare.pw.utc.com. You may view this service information at the 
FAA, Airworthiness Products Section, Operational Safety Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call (781) 238-7759.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0129; 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 NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Nicholas Paine, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7742; fax: (781) 238-7199; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0129; Project Identifier 
AD-2020-01597-E'' at the beginning of your comments. The most helpful 
comments

[[Page 13226]]

reference a specific portion of the proposal, 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 
proposal because of those comments.
    The FAA has been informed that IAE has done some outreach with 
affected operators regarding the proposed corrective actions for this 
unsafe condition. As a result, affected operators are already aware of 
the proposed corrective actions and, in some cases, have already begun 
planning for implementation. Therefore, the FAA has determined that a 
30-day comment period is appropriate given the particular circumstances 
related to the proposed correction of this unsafe condition.
    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 NPRM.

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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to 
Nicholas Paine, Aviation Safety Engineer, ECO Branch, FAA, 1200 
District Avenue, Burlington, MA 01803. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Background

    On March 18, 2020, an Airbus Model A321-231 airplane, powered by 
IAE V2533-A5 model turbofan engines, experienced an uncontained HPT 
1st-stage disk failure that resulted in an aborted takeoff. The 
uncontained failure of the HPT 1st-stage disk resulted in high-energy 
debris penetrating the engine cowling. The FAA published Emergency AD 
2020-07-51 on March 21, 2020 (followed by publication in the Federal 
Register on April 13, 2020, as a Final Rule, Request for Comments (85 
FR 20402)) and AD 2021-01-03 on January 6, 2021 (86 FR 458), to remove 
from service HPT 1st-stage and HPT 2nd-stage disks identified as having 
the highest risk of failure. Based on the root cause analysis performed 
since that event, the manufacturer identified a population of HPT 1st-
stage disks and HPT 2nd-stage disks that require inspection and 
possible removal from service. This condition, if not addressed, could 
result in uncontained HPT disk failure, damage to the engine, damage to 
the airplane, and loss of the airplane.

FAA's Determination

    The FAA is issuing this NPRM after determining that the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed IAE Non-Modification Service Bulletin (NMSB) No. 
V2500-ENG-72-0713, Revision 1, dated January 26, 2021. The NMSB 
identifies the affected HPT 1st-stage disks and HPT 2nd-stage disks on 
IAE V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, 
V2528-D5, V2530-A5, and V2533-A5 model turbofan engines and specifies 
procedures for a USI of the HPT 1st-stage disk and HPT 2nd-stage disk.
    The FAA also reviewed IAE NMSB No. V2500-E5-72-0015, dated December 
15, 2020. The NMSB identifies the affected HPT 1st-stage disks and HPT 
2nd-stage disks on IAE V2531-E5 model turbofan engines and specifies 
procedures for a USI of the HPT 1st-stage disk and HPT 2nd-stage disk.
    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.

Proposed AD Requirements in This NPRM

    This proposed AD would require the performance of a USI of the HPT 
1st-stage disk and HPT 2nd-stage disk and, depending on the results of 
the inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage 
disk with a part eligible for installation.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 1,100 engines installed on airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
USI the HPT 1st-stage disk and HPT    20 work-hours x $85 per              $0           $1,700       $1,870,000
 2nd-stage disk.                       hour = $1,700.
----------------------------------------------------------------------------------------------------------------

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

[[Page 13227]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace the HPT 1st-stage disk or HPT 2nd-     0 work-hours x $85 per hour =          $300,000         $300,000
 stage disk.                                    $0.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this 
proposed 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.

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

International Aero Engines AG: Docket No. FAA-2021-0129; Project 
Identifier AD-2020-01597-E.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by April 7, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to International Aero Engines AG (IAE) V2522-A5, 
V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-
A5, V2531-E5, and V2533-A5 model turbofan engines with an installed:
    (1) High-pressure turbine (HPT) 1st-stage disk, part number (P/
N) 2A5001, with a serial number (S/N) listed in Appendix A, Table 1, 
of IAE Non-Modification Service Bulletin (NMSB) No. V2500-ENG-72-
0713, Revision 1, dated January 26, 2021 (IAE NMSB V2500-ENG-72-
0713, Revision 1) or IAE NMSB No. V2500-E5-72-0015, dated December 
15, 2020 (IAE NMSB V2500-E5-72-0015); and/or
    (2) HPT 2nd-stage disk, P/N 2A4802, with an S/N listed in 
Appendix A, Table 2, of IAE NMSB V2500-ENG-72-0713, Revision 1, or 
IAE NMSB V2500-E5-72-0015.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by an analysis performed by the 
manufacturer after an event involving an uncontained failure of a 
HPT 1st-stage disk that resulted in high-energy debris penetrating 
the engine cowling. The FAA is issuing this AD to prevent failure of 
the HPT 1st-stage disk and HPT 2nd-stage disk. The unsafe condition, 
if not addressed, could result in uncontained HPT disk failure, 
damage to the engine, damage to the airplane, and loss of the 
airplane.

(f) Compliance

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

(g) Required Actions

    (1) For IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-
A5 model turbofan engines with an HPT 1st-stage disk, P/N 2A5001, 
with an S/N listed in Appendix A, Table 1, of IAE NMSB V2500-ENG-72-
0713, Revision 1, at the next engine shop visit after the effective 
date of this AD or before the HPT 1st-stage disk has accumulated 
3,200 flight cycles (FCs) since the effective date of this AD, 
whichever occurs first, perform an ultrasonic inspection (USI) of 
the HPT 1st-stage disk using the Accomplishment Instructions, 
paragraph 6, of IAE NMSB V2500-ENG-72-0713, Revision 1.
    (2) For IAE V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-
A5 model turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, 
with an S/N listed in Appendix A, Table 2, of IAE NMSB V2500-ENG-72-
0713, Revision 1, at the next engine shop visit after the effective 
date of this AD or before the HPT 2nd-stage disk has accumulated 
3,200 FCs since the effective date of this AD, whichever occurs 
first, perform a USI of the HPT 2nd-stage disk using the 
Accomplishment Instructions, paragraph 7, of IAE NMSB V2500-ENG-72-
0713, Revision 1.
    (3) For IAE V2522-A5, V2524-A5, V2525-D5, and V2527-A5 model 
turbofan engines with an HPT 1st-stage disk, P/N 2A5001, with an S/N 
listed in Appendix A, Table 1, of IAE NMSB V2500-ENG-72-0713, 
Revision 1, at the next HPT rotor and stator assembly (HPT module) 
removal or before the HPT 1st-stage disk has accumulated 6,700 FCs 
since the effective date of this AD, whichever occurs first, perform 
a USI of the HPT 1st-stage disk using the Accomplishment 
Instructions, paragraph 6, of IAE NMSB V2500-ENG-72-0713, Revision 
1.
    (4) For IAE V2522-A5, V2524-A5, V2525-D5, and V2527-A5 model 
turbofan engines with an HPT 2nd-stage disk, P/N 2A4802, with an S/N 
listed in Appendix A, Table 2, of IAE NMSB V2500-ENG-72-0713, 
Revision 1, at the next HPT module removal or before the HPT 2nd-
stage disk has accumulated 6,700 FCs since the effective date of 
this AD, whichever occurs first, perform a USI of the HPT 2nd-stage 
disk using the Accomplishment Instructions, paragraph 7, of IAE NMSB 
V2500-ENG-72-0713, Revision 1.
    (5) For IAE V2531-E5 model turbofan engines with an HPT 1st-
stage disk, P/N

[[Page 13228]]

2A5001, with an S/N listed in Appendix A, Table 1, of IAE NMSB 
V2500-E5-72-0015, at the next engine shop visit or before the HPT 
1st-stage disk has accumulated 3,200 FCs since the effective date of 
this AD, whichever occurs first, perform a USI of the HPT 1st-stage 
disk using the Accomplishment Instructions, paragraph 6, of IAE NMSB 
V2500-E5-72-0015.
    (6) For IAE V2531-E5 model turbofan engines with an HPT 2nd-
stage disk, P/N 2A4802, with an S/N listed in Appendix A, Table 2, 
of IAE NMSB V2500-E5-72-0015, at the next engine shop visit or 
before the HPT 2nd-stage disk has accumulated 3,200 FCs since the 
effective date of this AD, whichever occurs first, perform a USI of 
the HPT 2nd-stage disk using the Accomplishment Instructions, 
paragraph 7, of IAE NMSB V2500-E5-72-0015.
    (7) If, during the USI required by paragraphs (g)(1) through (6) 
of this AD, a HPT 1st-stage disk or HPT 2nd-stage disk does not pass 
the inspection as specified in the Accomplishment Instructions, 
paragraph 8., of IAE NMSB V2500-ENG-72-0713, Revision 1, or IAE NMSB 
V2500-E5-72-0015, as applicable, before further flight, remove the 
HPT 1st-stage disk or 2nd-stage disk, as applicable, from service 
and replace with a part eligible for installation.

(h) Definition

    For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, H-P, except for 
the following situations, which do not constitute an engine shop 
visit.
    (1) Separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance.
    (2) Engine removal for the purpose of performing field 
maintenance activities at a maintenance facility in lieu of 
performing them on-wing.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
certification office, send it to the attention of the person 
identified in Related Information. You may email your request 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.

(j) Related Information

    (1) For more information about this AD, contact Nicholas Paine, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7742; fax: (781) 238-7199; 
email: [email protected].
    (2) For service information identified in this AD, contact 
International Aero Engines AG, 400 Main Street, East Hartford, CT 
06118; phone: (800) 565-0140; email: [email protected]; website: 
http://fleetcare.pw.utc.com. You may view this referenced service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 1200 District Avenue, Burlington, MA 01803. For 
information on the availability of this material at the FAA, call 
(781) 238-7759.

    Issued on February 24, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-04236 Filed 3-5-21; 8:45 am]
BILLING CODE 4910-13-P