Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines, 82302-82305 [2020-27897]

Download as PDF 82302 Federal Register / Vol. 85, No. 244 / Friday, December 18, 2020 / Rules and Regulations information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA 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 (j)(2) of this AD and as specified in paragraph (i) of this AD, if any service information referenced in EASA AD 2020–0258 contains paragraphs that are labeled as RC, the instructions in RC paragraphs, including subparagraphs under an RC paragraph, must be done to comply with this AD; any paragraphs, including subparagraphs under those paragraphs, that are not identified as RC are recommended. The instructions in paragraphs, including subparagraphs under those paragraphs, 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 instructions identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to instructions identified as RC require approval of an AMOC. khammond on DSKJM1Z7X2PROD with RULES (k) Related Information For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on January 4, 2021. (i) European Union Aviation Safety Agency (EASA) AD 2020–0258, dated November 18, 2020; corrected November 19, 2020. (ii) [Reserved] (4) For EASA AD 2020–0258, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. (5) You may view this material at the FAA, Airworthiness Products Section, Operational VerDate Sep<11>2014 19:27 Dec 17, 2020 Jkt 253001 Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. This material may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020–1121. (6) 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 fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Issued on December 7, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–27975 Filed 12–15–20; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–1032; Project Identifier MCAI–2020–00856–E; Amendment 39–21338; AD 2020–24–08] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by RollsRoyce plc) Turbofan Engines Examining the AD Docket Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 768–60, 772–60, 772B–60 and 772C–60 model turbofan engines. This AD requires replacement of high-pressure turbine (HPT) blades with parts eligible for installation before exceeding specified flight cycles since new. This AD was prompted by several reports from the manufacturer that HPT blades on RB211 Trent 700 model turbofan engines have been subject to high levels of corrosion fatigue, leading to blade cracking and eventual release, resulting in an aborted take-off and in-flight shutdowns. The FAA is issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective January 4, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 4, 2021. DATES: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 The FAA must receive comments on this AD by February 1, 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 final rule, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom, phone: +44 (0)1332 242424; website: https://www.rolls-royce.com/ contact-us.aspx. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238– 7759. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 1032. You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–1032; 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 street address for the Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238– 7199; email: Scott.M.Stevenson@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2018–0291, dated December 21, 2018 (referred to after this as ‘‘the MCAI’’), to address the unsafe condition for the specified products. The MCAI states: HP turbine blades on a number of Trent 700 engines have been subject to high levels of corrosion fatigue, leading to blade cracking and eventual release. This has caused a E:\FR\FM\18DER1.SGM 18DER1 Federal Register / Vol. 85, No. 244 / Friday, December 18, 2020 / Rules and Regulations number of aborted take-off and in-flight shutdown events. Sampling has identified that corrosion fatigue affects blades at varying rates, likely dependent on environmental, operational and individual blade conditions. This condition, if not corrected, could lead to blade failure and subsequent increased risk of high energy debris release, possibly resulting in damage to, and reduced control of, the aeroplane. To address this potential unsafe condition, RR issued the NMSB to provide instructions for removal from service of certain engines where a higher level of corrosion exposure is expected for the affected blades. For the reason described above, this [EASA] AD requires removal from service of certain engines, to be corrected in shop. You may obtain further information by examining the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–1032. Related Service Information Under 1 CFR Part 51 The FAA reviewed Rolls-Royce RB211 Trent 700 Series Alert NonModification Service Bulletin (NMSB) RB.211–72–AK165, dated November 26, 2018. The Alert NMSB describes procedures for removal of specific engines, identified by serial number, to enable replacement of potentially corrosion-fatigued HPT blades. The FAA also reviewed Task 72–41–52– 200–800—General Data for the Inspection of the High Pressure (HP) Turbine Blades, dated June 10, 2011, from the (Rolls-Royce) RR Trent-768– 60/15 Engine Manual. This Task describes procedures for inspection of the HPT blades. 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. FAA’s Determination khammond on DSKJM1Z7X2PROD with RULES This product has been approved by EASA and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. The FAA is issuing this AD because it evaluated all the relevant information provided by EASA and determined that the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires replacement of HPT blades on affected engines prior to accumulating a specified number of flight cycles since new, or before further flight, whichever occurs later. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than 30 days, upon a finding of good cause. The FAA has found the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because no domestic operators use this product. It is unlikely that the FAA will receive any adverse comments or useful information about this AD from U.S. operators. Accordingly, notice and opportunity for prior public comment are unnecessary, pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the foregoing reasons, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, the FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the FAA– 2020–1032 and Project Identifier MCAI– 2020–00856–E at the beginning of your comments. The most helpful comments 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 82303 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 FAA 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 final rule 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 final rule, 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 final rule. Submissions containing CBI should be sent to Scott Stevenson, 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. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 0 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Remove and replace HPT blades .................. 52 work hours × $85 per hour = $4,420 ........ $1,500,000 $1,504,420 $0 VerDate Sep<11>2014 19:27 Dec 17, 2020 Jkt 253001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\18DER1.SGM 18DER1 82304 Federal Register / Vol. 85, No. 244 / Friday, December 18, 2020 / Rules and Regulations 21338; Docket No. FAA–2020–1032; Project Identifier MCAI–2020–00856–E. 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 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, and (2) Will not affect intrastate aviation in Alaska. 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: ■ khammond on DSKJM1Z7X2PROD with RULES 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 (AD): ■ 2020–24–08 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc): Amendment 39– VerDate Sep<11>2014 19:27 Dec 17, 2020 Jkt 253001 (a) Effective Date This AD is effective January 4, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 768–60, 772–60, 772B–60, and 772C–60 model turbofan engines with an engine serial number (ESN) identified in Table 1 or Table 2 of Appendix 1 of RollsRoyce (RR) RB211 Trent 700 Series Alert Non-Modification Service Bulletin RB.211– 72–AK165, dated November 26, 2018 (the NMSB). (d) Subject Joint Aircraft System Component (JASC) Code/Air Transport Association (ATA) of America Code 7250—Turbine Section. (e) Unsafe Condition This AD was prompted by a determination by the manufacturer that high-pressure turbine (HPT) blades on several RB211 Trent 700 model turbofan engines have been subject to high levels of corrosion fatigue, leading to HPT blade cracking and eventual release. The FAA is issuing this AD to prevent failure of the HPT blades. The unsafe condition, if not addressed, could result in blade failure and subsequent release of highenergy debris, possibly resulting in damage to, and reduced control of, the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For engines with an ESN listed in Table 1 of Appendix 1 of the NMSB, prior to each HPT blade accumulating 3,500 flight cycles since new, or before further flight after the effective date of this AD, whichever occurs later, remove the HPT blade from service and replace with a part eligible for installation. (2) For engines with an ESN listed in Table 2 of Appendix 1 of the NMSB, prior to each HPT blade accumulating 5,800 flight cycles since new, or before further flight after the effective date of this AD, whichever occurs later, remove the HPT blade from service and replace with a part eligible for installation. (3) If the flight cycles since new of an HPT blade are unable to be determined, use the flight cycles since new, flight cycles since refurbishment, or flight cycles since overhaul of the HPT module. (h) Definition For the purpose of this AD, ‘‘a part eligible for installation’’ is: (1) An HPT blade that has: (i) Been removed from an engine with a serial number listed in Table 1 of the NMSB; and (ii) not exceeded 3,500 flight cycles since new; and (iii) before installation, passed an inspection (no crack detected) in accordance PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 with Task 72–41–52–200–800—General Data for the Inspection of the High Pressure (HP) Turbine Blades, dated June 10, 2011, from the (Rolls-Royce) RR Trent-768–60/15 Engine Manual (RR Task 72–41–52–200–800); or (2) An HPT blade that has: (i) Been removed from an engine with a serial number listed in Table 2 of the NMSB; and (ii) not exceeded 5,800 flight cycles since new; and (iii) before installation, passed an inspection (no crack detected) in accordance with Task 72–41–52–200–800—General Data for the Inspection of the High Pressure (HP) Turbine Blades, dated June 10, 2011, from the RR Trent-768–60/15 Engine Manual (RR Task 72–41–52–200–800); or (3) An HPT blade with zero flight cycles since new. (i) No Reporting Requirements The reporting requirements specified in paragraph R. of RR Task 72–41–52–200–800 are not required by this AD. (j) 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. (k) Related Information (1) For more information about this AD, contact Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238–7199; email: Scott.M.Stevenson@faa.gov. (2) Refer to European Aviation Safety Agency (EASA) AD No. 2018–0291, dated December 21, 2018, for more information. You may examine the EASA AD in the AD docket at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2018–1032. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Rolls-Royce RB211 Trent 700 Series Alert Non-Modification Service Bulletin RB.211–72–AK165, dated November 26, 2018. (ii) Task 72–41–52–200–800—General Data for the Inspection of the High Pressure (HP) Turbine Blades, dated June 10, 2011, from E:\FR\FM\18DER1.SGM 18DER1 Federal Register / Vol. 85, No. 244 / Friday, December 18, 2020 / Rules and Regulations the (Rolls-Royce) RR Trent-768–60/15 Engine Manual. (3) For service information identified in this AD, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom, phone: +44 (0)1332 242424; website: https:// www.rolls-royce.com/contact-us.aspx. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on November 17, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2020–27897 Filed 12–17–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0572; Product Identifier 2017–SW–056–AD; Amendment 39–21358; AD 2020–26–03] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2007–26– 51 which applied to certain Airbus Helicopters Deutschland GmbH Model EC135 helicopters. AD 2007–26–51 required inspecting the tail rotor control rod (control rod) and ball pivot and, depending on findings, replacing those parts. This new AD requires inspecting certain ball pivots, applying corrosion preventative compound on the ball pivot, and corrective action, as applicable. This AD also requires replacing the control rod with a newly developed control rod. This AD was prompted by the manufacturer’s development of a new control rod, which the FAA has determined must be installed in order to address the identified unsafe condition. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective January 22, 2021. khammond on DSKJM1Z7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 19:27 Dec 17, 2020 Jkt 253001 The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 22, 2021. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972–641–0000 or 800–232– 0323; fax 972–641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0572. You may examine the AD docket on the internet at https:// www.regulations.gov in Docket No. FAA–2020–0572; 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 European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, any service information that is incorporated by reference, 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: David Hatfield, Aviation Safety Engineer, Aircraft Systems Section, Technical Innovation Policy Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222– 5116; email David.Hatfield@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2007–26–51, Amendment 39–15357 (73 FR 6008, February 1, 2008) (AD 2007–26–51), and add a new AD. AD 2007–26–51 applied to certain Airbus Helicopters Deutschland GmbH (type certificate previously held by Eurocopter Deutschland GmbH) Model EC135 helicopters, serial number (S/N) 0005 up to and including S/N 0444, except S/ N 0028, and with control rod part number (P/N) L672M2005207, installed. The NPRM was published in the Federal Register on June 18, 2020 (85 FR 36816). The NPRM proposed to require inspecting certain ball pivots for PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 82305 damage and freedom of movement, applying corrosion preventative compound on the ball pivot, and corrective action, as applicable. The NPRM also proposed to require replacing the control rod with the newly developed control rod that the FAA determined was necessary to address the unsafe condition. The NPRM was prompted by EASA AD No. 2010–0227R1, dated April 7, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for all Model EC135 P1, EC135 P2, EC135 P2+, EC135 T1, EC 135 T2, and EC135 T2+ helicopters; and Model EC635 T1, EC635 P2+, and EC635 T2+ helicopters. EASA advises that in 2007 an accident occurred on an EC135 helicopter in Japan. Preliminary investigation results indicated that loss of control was due to failure of the control rod. EASA issued EASA Emergency AD 2007–0301–E, dated December 13, 2007 (EASA AD 2007– 0301–E) to inspect the affected control rod P/N L672M2005207 and the ball pivot (which correspond to the actions required by AD 2007–26–51). EASA AD 2007–0301–E was subsequently superseded by EASA AD 2007–0313, dated December 21, 2007, to require repetitive inspections and, depending on findings, the replacement of the control rod and ball pivot, only for helicopters not equipped with an automatic flight control system (AFCS). After review of the inspection results, EASA issued EASA AD 2008–0064, dated April 4, 2008, and later revised to EASA AD 2008–0064 R1, dated April 15, 2008 (EASA AD 2008–0064 R1), to apply the requirements to helicopters equipped with an AFCS. EASA also advises that after EASA AD 2008–0064R1 was issued, Eurocopter Deutschland GmbH developed a new control rod P/N L672M2006101, installation of which constituted terminating action for the repetitive inspections. Consequently, EASA issued EASA AD 2010–0227, dated November 3, 2010, and corrected November 8, 2010, retaining the requirements of EASA AD 2008– 0064R1, and requiring the replacement of control rod P/N L672M2005207 with the new control rod P/N L672M2006101. The FAA has determined that this new control rod must be installed in order to address the unsafe condition. In addition, EASA advises that following a review of data and feedback received from in-service helicopters, it E:\FR\FM\18DER1.SGM 18DER1

Agencies

[Federal Register Volume 85, Number 244 (Friday, December 18, 2020)]
[Rules and Regulations]
[Pages 82302-82305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27897]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1032; Project Identifier MCAI-2020-00856-E; 
Amendment 39-21338; AD 2020-24-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
(Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Rolls-Royce Deutschland Ltd & Co KG (Type Certificate 
Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 768-60, 772-60, 
772B-60 and 772C-60 model turbofan engines. This AD requires 
replacement of high-pressure turbine (HPT) blades with parts eligible 
for installation before exceeding specified flight cycles since new. 
This AD was prompted by several reports from the manufacturer that HPT 
blades on RB211 Trent 700 model turbofan engines have been subject to 
high levels of corrosion fatigue, leading to blade cracking and 
eventual release, resulting in an aborted take-off and in-flight shut-
downs. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective January 4, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 4, 
2021.
    The FAA must receive comments on this AD by February 1, 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 final rule, contact 
Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom, phone: 
+44 (0)1332 242424; website: https://www.rolls-royce.com/contact-us.aspx. You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call (781) 238-7759. It is 
also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2020-1032.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-1032; 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 street address for the 
Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7132; fax: (781) 238-7199; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No. 2018-0291, dated December 21, 2018 (referred to after this as 
``the MCAI''), to address the unsafe condition for the specified 
products. The MCAI states:

    HP turbine blades on a number of Trent 700 engines have been 
subject to high levels of corrosion fatigue, leading to blade 
cracking and eventual release. This has caused a

[[Page 82303]]

number of aborted take-off and in-flight shut-down events. Sampling 
has identified that corrosion fatigue affects blades at varying 
rates, likely dependent on environmental, operational and individual 
blade conditions.
    This condition, if not corrected, could lead to blade failure 
and subsequent increased risk of high energy debris release, 
possibly resulting in damage to, and reduced control of, the 
aeroplane.
    To address this potential unsafe condition, RR issued the NMSB 
to provide instructions for removal from service of certain engines 
where a higher level of corrosion exposure is expected for the 
affected blades.
    For the reason described above, this [EASA] AD requires removal 
from service of certain engines, to be corrected in shop.

    You may obtain further information by examining the MCAI in the AD 
docket at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2020-1032.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Rolls-Royce RB211 Trent 700 Series Alert Non-
Modification Service Bulletin (NMSB) RB.211-72-AK165, dated November 
26, 2018. The Alert NMSB describes procedures for removal of specific 
engines, identified by serial number, to enable replacement of 
potentially corrosion-fatigued HPT blades. The FAA also reviewed Task 
72-41-52-200-800--General Data for the Inspection of the High Pressure 
(HP) Turbine Blades, dated June 10, 2011, from the (Rolls-Royce) RR 
Trent-768-60/15 Engine Manual. This Task describes procedures for 
inspection of the HPT blades. 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.

FAA's Determination

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

AD Requirements

    This AD requires replacement of HPT blades on affected engines 
prior to accumulating a specified number of flight cycles since new, or 
before further flight, whichever occurs later.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C.) authorizes agencies to dispense with notice and comment 
procedures for rules when the agency, for ``good cause,'' finds that 
those procedures are ``impracticable, unnecessary, or contrary to the 
public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than 30 days, upon 
a finding of good cause.
    The FAA has found the risk to the flying public justifies waiving 
notice and comment prior to adoption of this rule because no domestic 
operators use this product. It is unlikely that the FAA will receive 
any adverse comments or useful information about this AD from U.S. 
operators. Accordingly, notice and opportunity for prior public comment 
are unnecessary, pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for 
the foregoing reasons, the FAA finds that good cause exists pursuant to 
5 U.S.C. 553(d) for making this amendment effective in less than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, the FAA invites you to send any written data, views, 
or arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the FAA-2020-1032 and 
Project Identifier MCAI-2020-00856-E at the beginning of your comments. 
The most helpful comments 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 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 FAA 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 final rule 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 final rule, 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 final rule. Submissions containing CBI 
should be sent to Scott Stevenson, 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.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 0 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Remove and replace HPT blades.......  52 work hours x $85 per      $1,500,000       $1,504,420               $0
                                       hour = $4,420.
----------------------------------------------------------------------------------------------------------------


[[Page 82304]]

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

    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, and
    (2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2020-24-08 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate 
Previously Held by Rolls-Royce plc): Amendment 39-21338; Docket No. 
FAA-2020-1032; Project Identifier MCAI-2020-00856-E.

(a) Effective Date

    This AD is effective January 4, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce Deutschland Ltd & Co KG (Type 
Certificate Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 
768-60, 772-60, 772B-60, and 772C-60 model turbofan engines with an 
engine serial number (ESN) identified in Table 1 or Table 2 of 
Appendix 1 of Rolls-Royce (RR) RB211 Trent 700 Series Alert Non-
Modification Service Bulletin RB.211-72-AK165, dated November 26, 
2018 (the NMSB).

(d) Subject

    Joint Aircraft System Component (JASC) Code/Air Transport 
Association (ATA) of America Code 7250--Turbine Section.

(e) Unsafe Condition

    This AD was prompted by a determination by the manufacturer that 
high-pressure turbine (HPT) blades on several RB211 Trent 700 model 
turbofan engines have been subject to high levels of corrosion 
fatigue, leading to HPT blade cracking and eventual release. The FAA 
is issuing this AD to prevent failure of the HPT blades. The unsafe 
condition, if not addressed, could result in blade failure and 
subsequent release of high-energy debris, possibly resulting in 
damage to, and reduced control of, the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For engines with an ESN listed in Table 1 of Appendix 1 of 
the NMSB, prior to each HPT blade accumulating 3,500 flight cycles 
since new, or before further flight after the effective date of this 
AD, whichever occurs later, remove the HPT blade from service and 
replace with a part eligible for installation.
    (2) For engines with an ESN listed in Table 2 of Appendix 1 of 
the NMSB, prior to each HPT blade accumulating 5,800 flight cycles 
since new, or before further flight after the effective date of this 
AD, whichever occurs later, remove the HPT blade from service and 
replace with a part eligible for installation.
    (3) If the flight cycles since new of an HPT blade are unable to 
be determined, use the flight cycles since new, flight cycles since 
refurbishment, or flight cycles since overhaul of the HPT module.

(h) Definition

    For the purpose of this AD, ``a part eligible for installation'' 
is:
    (1) An HPT blade that has:
    (i) Been removed from an engine with a serial number listed in 
Table 1 of the NMSB; and
    (ii) not exceeded 3,500 flight cycles since new; and
    (iii) before installation, passed an inspection (no crack 
detected) in accordance with Task 72-41-52-200-800--General Data for 
the Inspection of the High Pressure (HP) Turbine Blades, dated June 
10, 2011, from the (Rolls-Royce) RR Trent-768-60/15 Engine Manual 
(RR Task 72-41-52-200-800); or
    (2) An HPT blade that has:
    (i) Been removed from an engine with a serial number listed in 
Table 2 of the NMSB; and
    (ii) not exceeded 5,800 flight cycles since new; and
    (iii) before installation, passed an inspection (no crack 
detected) in accordance with Task 72-41-52-200-800--General Data for 
the Inspection of the High Pressure (HP) Turbine Blades, dated June 
10, 2011, from the RR Trent-768-60/15 Engine Manual (RR Task 72-41-
52-200-800); or
    (3) An HPT blade with zero flight cycles since new.

(i) No Reporting Requirements

    The reporting requirements specified in paragraph R. of RR Task 
72-41-52-200-800 are not required by this AD.

(j) 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.

(k) Related Information

    (1) For more information about this AD, contact Scott Stevenson, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7132; fax: (781) 238-7199; 
email: [email protected].
    (2) Refer to European Aviation Safety Agency (EASA) AD No. 2018-
0291, dated December 21, 2018, for more information. You may examine 
the EASA AD in the AD docket at https://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2018-1032.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Rolls-Royce RB211 Trent 700 Series Alert Non-Modification 
Service Bulletin RB.211-72-AK165, dated November 26, 2018.
    (ii) Task 72-41-52-200-800--General Data for the Inspection of 
the High Pressure (HP) Turbine Blades, dated June 10, 2011, from

[[Page 82305]]

the (Rolls-Royce) RR Trent-768-60/15 Engine Manual.
    (3) For service information identified in this AD, contact 
Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom, 
phone: +44 (0)1332 242424; website: https://www.rolls-royce.com/contact-us.aspx.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on November 17, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-27897 Filed 12-17-20; 8:45 am]
BILLING CODE 4910-13-P