Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 18849-18852 [2017-07983]

Download as PDF Federal Register / Vol. 82, No. 77 / Monday, April 24, 2017 / Rules and Regulations (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0238, dated December 18, 2015, 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–2016–7269. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Alert Operators Transmission A53W010–15, Revision 01, including Appendixes 1, 2, 3, and 4, dated October 4, 2016. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on April 13, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–07981 Filed 4–21–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–1015; Directorate Identifier 2013–NE–37–AD; Amendment 39– 18859; AD 2017–08–10] jstallworth on DSK7TPTVN1PROD with RULES RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: VerDate Sep<11>2014 13:01 Apr 21, 2017 Jkt 241001 We are superseding airworthiness directive (AD) 2017–01– 01 for all Rolls-Royce plc (RR) RB211– Trent 970–84, RB211–Trent 970B–84, RB211–Trent 972–84, RB211–Trent 972B–84, RB211–Trent 977–84, RB211– Trent 977B–84, and RB211–Trent 980– 84 turbofan engines. AD 2017–01–01 required inspections of the low-pressure turbine (LPT) exhaust case and support assembly or tail bearing housing (TBH) to detect cracks or damage. This AD corrects references to certain service bulletins in the compliance section of AD 2017–01–01. This AD was prompted by reports that references to service bulletins in AD 2017–01–01 are incorrect. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective May 9, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 26, 2017 (82 FR 3146, January 11, 2017). We must receive any comments on this AD by June 8, 2017. 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44–1332–242424; fax: 011–44– 1332–245418, or email: https:// www.rolls-royce.com/contact/civil_ team.jsp. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2013– 1015. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 18849 www.regulations.gov by searching for and locating Docket No. FAA–2013– 1015; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the mandatory continuing airworthiness information, regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7754; fax: 781–238–7199; email: robert.green@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2013–1015; Directorate Identifier 2013– NE–37–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Discussion On December 22, 2016, we issued AD 2017–01–01, Amendment 39–18768 (82 FR 3146, January 11, 2017), for all RR RB211–Trent 970–84, RB211–Trent 970B–84, RB211–Trent 972–84, RB211– Trent 972B–84, RB211–Trent 977–84, RB211–Trent 977B–84, and RB211– Trent 980–84 turbofan engines. AD 2017–01–01 required inspections of the LPT exhaust case and support assembly or TBH to detect cracks or damage. AD 2017–01–01 resulted from RR performing additional analysis of inspection results and determining that the existing inspections need to be modified. We issued AD 2017–01–01 to E:\FR\FM\24APR1.SGM 24APR1 18850 Federal Register / Vol. 82, No. 77 / Monday, April 24, 2017 / Rules and Regulations prevent failure of the TBH, resulting in damage to the engine and to the airplane. Actions Since AD 2017–01–01 Was Issued Since we issued AD 2017–01–01, we learned that certain references to certain service bulletins in AD 2017–01–01 are incorrect. In the fourth row, second column of Table 2 to paragraph (f) of AD 2017–01–01, the applicable Alert NonModification Service Bulletin (NMSB) states ‘‘RB.211–72–AJ101’’ but the correct reference is ‘‘RB.211–72– AH154.’’ In addition, two references to ‘‘NMSB RB.211–72–J024’’ in Table 1 and Table 2 to paragraph (f) of AD 2017–01–01 should say ‘‘SB RB.211–72– J024’’. We have corrected those references in this AD. Related Service Information Under 1 CFR Part 51 RR has issued Alert NMSB RB.211– 72–AG971, Revision 2, dated May 5, 2016; Alert NMSB RB.211–72–AH154, Revision 5, dated May 5, 2016; Alert NMSB RB.211–72–AJ101, dated May 5, 2016; and Service Bulletin (SB) RB.211– 72–J055, dated March 22, 2016. RR Alert NMSB RB.211–72–AG971 describes procedures for on-wing or in-shop inspection of the TBH mount lug runouts. RR Alert NMSB RB.211–72– AH154 describes procedures for an onwing or in-shop inspection of a pre-mod 72–J024 TBH. RR Alert NMSB RB.211– 72–AJ101 describes procedures for onwing or in-shop inspection of a postmod 72–J024 TBH. RR SB RB.211–72– J055 describes procedures for modifying the engine by introducing a revised TBH. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires inspections of the LPT exhaust case and support assembly or TBH to detect cracks or damage. FAA’s Justification and Determination of the Effective Date No domestic operators use this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Costs of Compliance We estimate that this AD affects 0 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection of the TBH ..................... 8 work-hours × $85 per hour = $680. Authority for This Rulemaking jstallworth on DSK7TPTVN1PROD with RULES 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. We are 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 VerDate Sep<11>2014 13:01 Apr 21, 2017 Jkt 241001 Parts cost Cost per product $0 $680 per inspection cycle .............. distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Cost on U.S. operators $0 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 removing airworthiness directive (AD) 2017–01–01, Amendment 39–18768 (82 FR 3146, January 11, 2017), and adding the following new AD: ■ 2017–08–10 Rolls-Royce plc: Amendment 39–18859; Docket No. FAA–2013–1015; Directorate Identifier 2013–NE–37–AD. (a) Effective Date This AD is effective May 9, 2017. (b) Affected ADs This AD replaces AD 2017–01–01, Amendment 39–18768 (82 FR 3146, January 11, 2017). (c) Applicability This AD applies to all Rolls-Royce plc (RR) RB211–Trent 970–84, RB211–Trent 970B–84, RB211–Trent 972–84, RB211–Trent 972B–84, RB211–Trent 977–84, RB211–Trent 977B–84, and RB211–Trent 980–84 turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7200, Engine (Turbine/Turboprop). E:\FR\FM\24APR1.SGM 24APR1 Federal Register / Vol. 82, No. 77 / Monday, April 24, 2017 / Rules and Regulations (e) Unsafe Condition This AD was prompted by reports that references to certain service bulletins are incorrect. We are issuing this AD to prevent failure of the tail bearing housing (TBH), resulting in damage to the engine and to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within the compliance times and using the service information specified in Table 1 to paragraph (f) of this AD, accomplish onwing inspections of the TBH features using the following instructions, as applicable. (i) If during any on-wing inspection of the TBH mount lug run-outs done using the Accomplishment Instructions, paragraph 3.A.(1), of RR Alert Non-Modification Service Bulletin (NMSB) RB.211–72–AG971, Revision 2, dated May 5, 2016, any cracks less than or equal to 2 mm in length are found, remove the engine from service within 10 flight cycles (FCs). If any cracks greater than 2 mm are found, remove the engine from service before further flight. (ii) If during any on-wing inspection of the TBH mount lug run-outs done using the Accomplishment Instructions, paragraph 3.A.(2), of RR Alert NMSB RB.211–72– AG971, Revision 2, dated May 5, 2016, any crack indications resulting in an inspection signal with an amplitude of 50% full screen height or more are found, remove the engine from service before further flight. (iii) If during any on-wing inspection of a pre-mod 72–J024 TBH, any crack or damage is found on the TBH mount lug forging leading edge (LE) areas, re-inspect the engine or remove the engine from service in accordance with the Accomplishment Instructions, paragraph 3.A.(3)(t), of RR Alert NMSB RB.211–72–AH154, Revision 5, dated May 5, 2016. (iv) If during any on-wing inspection of a post-mod 72–J024 TBH, any crack is found on the TBH mount lug forging LE or cutback areas, re-inspect the engine or remove the engine from service in accordance with the Accomplishment Instructions, paragraph 3.A.(3)(t), of RR Alert NMSB RB.211–72– AJ101, dated May 5, 2016. (2) Within the compliance times and using the service information specified in Table 2 to paragraph (f) of this AD, perform in-shop inspections of the TBH features using the following instructions, as applicable. (i) If during any in-shop inspection of the TBH, any crack is found on the TBH mount lug or central male catcher run-outs, replace the TBH with a TBH eligible for installation before the engine is returned to service. 18851 (ii) If during any in-shop inspection of the TBH, any crack is found on the top core vanes, reject as unserviceable or repair the TBH in accordance with the Accomplishment Instructions, paragraph 3.C.(1)(f), of RR Alert NMSB RB.211–72– AG971 Revision 2, dated May 5, 2016, before the engine is returned to service. (iii) If during any in-shop inspection of a pre-mod 72–J024 TBH, any crack or damage is found on the TBH mount lug forging LE areas, reject as unserviceable or repair the TBH in accordance with the Accomplishment Instructions, paragraph 3.B.(2)(u)(ii), of RR Alert NMSB RB.211–72– AH154, Revision 5, dated May 5, 2016, or the Accomplishment Instructions, paragraph 3.C.(1)(f), of RR Alert NMSB RB.211–72– AG971, Revision 2, dated May 5, 2016, before the engine is returned to service. (iv) If during any in-shop inspection of a post-mod 72–J024 TBH, any crack is found on the TBH mount lug forging LE or cutback areas, repair the TBH in accordance with the Accomplishment Instructions, paragraph 3.B.(2)(u)(ii), of RR Alert NMSB RB.211–72– AJ101, dated May 5, 2016, or the Accomplishment Instructions, paragraph 3.C.(1)(f), of Alert NMSB RB.211–72–AG971, Revision 2, dated May 5, 2016, before the engine is returned to service. TABLE 1 TO PARAGRAPH (f)—TBH ON-WING INSPECTIONS Repeat inspection interval (not to exceed) Affected TBH P/N and feature Applicable NMSB and paragragph Alternate NMSB instructions acceptable for prior compliance All—Mount Lug Run-outs ........ RB.211–72–AG971, Revision 2, Paragraph 3.A. Before exceeding 2,200 FCs since new. 2,200 FCs. Pre-mod 72–J024 TBH— Mount Lug Forging LE Areas—for a TBH that has not exceeded 900 FCs since new on April 7, 2014. Pre-mod 72–J024 TBH— Mount Lug Forging LE Areas—for a TBH that has exceeded 900 FCs since new on April 7, 2014. Post-mod 72–J024 TBH— Mount Lug Forging LE and Cutback Areas. RB.211–72–AH154, Revision 5, Paragraph 3.A. In-shop: RB.211–72–AG971, Revision 2, Paragraph 3.B or 3.C. In-shop: RB.211–72–AH154, Revision 5, Paragraph 3.B., or RB.211-72–AG971, Revision 2, Paragraph 3.C. Before exceeding 1,000 FCs since new. 1,000 FCs. RB.211–72–AH154, Revision 5, Paragraph 3.A. In-shop: RB.211–72–AH154, Revision 5, Paragraph 3.B., or RB.211-72–AG971, Revision 2, Paragraph 3.C. Within 100 FCs after April 7, 2014. 1,000 FCs. RB.211–72–AJ101, Paragraph 3.A. In-shop: RB.211–72–AG971, Revison 2, Paragraph 3.C, or RB.211–72–AJ101, Paragraph 3.B. Before exceeding 1,000 FCs since SB RB.211-72-J024 embodiment. 1,000 FCs. Initial inspection TABLE 2 TO PARAGRAPH (f)—TBH IN-SHOP INSPECTIONS Applicable NMSB and paragraph Alternate NMSB instructions acceptable for prior compliance All—Mount Lug Run-outs ........ jstallworth on DSK7TPTVN1PROD with RULES Affected TBH P/N and feature RB.211–72–AG971, Revision 2, Paragraph 3. All—Top Core Vanes and Central Male Catcher Run-outs. RB.211–72–AG971, Revision 2, Paragraph 3.C. On-wing: RB.211–72–AG971, Revision 2, Paragraph 3.A., or In-shop: RB.211–72–AG971, Revision 2, Paragraph 3.C. None ....................................... VerDate Sep<11>2014 16:34 Apr 21, 2017 Jkt 241001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Initial inspection Repeat inspection interval (not to exceed) Before exceeding 2,200 flight FCs since new. 2,200 FCs. Before exceeding 3,800 FCs since new. 3,800 FCs. E:\FR\FM\24APR1.SGM 24APR1 18852 Federal Register / Vol. 82, No. 77 / Monday, April 24, 2017 / Rules and Regulations TABLE 2 TO PARAGRAPH (f)—TBH IN-SHOP INSPECTIONS—Continued Affected TBH P/N and feature Pre-mod 72–J024 TBH— Mount Lug Forging LE Areas—for a TBH that has not exceeded 900 FCs since new on April 7, 2014. Pre-mod 72–J024 TBH— Mount Lug Forging LE Areas—for a TBH that has exceeded 900 FCs since new on April 7, 2014. Post-mod 72–J024 TBH— Mount Lug Forging LE and Cutback Areas. Applicable NMSB and paragraph jstallworth on DSK7TPTVN1PROD with RULES Repeat inspection interval (not to exceed) On-wing: RB.211–72–AH154, Revision 5, Section 3.A, or In-shop: RB.211–72–AG971, Revision 2, Paragraph 3.C. Before exceeding 1,000 FCs since new. 1,000 FCs. RB.211–72–AH154, Revision 5, Paragraph 3.B. On-wing: RB.211–72–AH154, Revision 5, Section 3.A, or In-shop: RB.211–72–AG971, Revision 2, Paragraph 3.C. Within 100 FCs after the effective date of this AD. 1,000 FCs. RB.211–72–AJ101, Paragraph 3.B. On-wing: RB.211–72–AJ101, Section 3.A, or In-shop: RB.211–72–AG971, Revision 2, Paragraph 3.C. Before exceeding 1,000 FCs since SB RB.211-72–J024 embodiment. 1,000 FCs. (1) If you performed inspections and corrective actions on an engine before the effective date of this AD, in accordance with earlier versions of RR Alert NMSB RB.211– 72–AG971, Revision 2, dated May 5, 2016, or RR Alert NMSB RB.211–72–AH154, Revision 5, dated May 5, 2016, you met the requirements of paragraph (f)(1) or (2) of this AD, as applicable. (2) If, on or before April 7, 2014, you performed the inspections and corrective actions required by paragraphs (f)(1) and (2) of this AD using RR Technical Variance (TV) No. 124801, Issue 2, dated July 4, 2012 or earlier versions; or RR TV No. 124851, Issue 2, dated July 4, 2012 or earlier versions; you met the requirements for a mount lug run-out inspection. (3) If, on or before April 7, 2014, you performed the inspections and corrective actions required by paragraphs (f)(1) and (2) of this AD using RR Repeater TV No. 132043, Issue 1, dated March 25, 2013 or earlier versions; or using RR Repeater TV No. 132217, Issue 5, dated May 23, 2013 or earlier versions; you met the requirements for the mount lug forging LE inspections of this AD. (h) Optional Terminating Action (1) Accomplishment of corrective actions required by paragraphs (f)(1) and (2) of this AD does not constitute terminating action for the repetitive inspections required by this AD. (2) Modification of an engine in accordance with the instructions of RR Service Bulletin RB.211–72–J055, dated March 22, 2016, constitutes terminating action for the repetitive inspections required by paragraphs (f)(1) and (2) of this AD for that engine, provided that, following this modification, no affected TBH is installed on that engine. (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. 16:34 Apr 21, 2017 Initial inspection RB.211–72–AH154, Revision 5, Paragraph 3.B. (g) Credit for Previous Actions VerDate Sep<11>2014 Alternate NMSB instructions acceptable for prior compliance Jkt 241001 (j) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7754; fax: 781–238–7199; email: robert.green@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2016–0193, dated September 30, 2016, for more information. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating it in Docket No. FAA–2013–1015. (3) RR TV No. 124801, Issue 2, dated July 4, 2012; RR TV No. 124851, Issue 2, dated July 4, 2012, Repeater TV No. 132043, Issue 1, dated March 25, 2013, and Repeater TV No. 132217, Issue 5, dated May 23, 2013; which are not incorporated by reference in this AD, can be obtained from RR using the contact information in paragraph (k)(3) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on January 26, 2017 (82 FR 3146, January 11, 2017). (i) Rolls-Royce plc (RR) Service Bulletin RB.211–72–J055, dated March 22, 2016. (ii) RR Alert Non-Modification Service Bulletin (NMSB) RB.211–72–AJ101, dated May 5, 2016; (iii) RR Alert NMSB RB.211–72–AG971, Revision 2, dated May 5, 2016; and (iv) RR Alert NMSB RB.211–72–AH154, Revision 5, dated May 5, 2016. (4) For RR service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–245418, or email: https://www.rolls-royce.com/contact/civil_ team.jsp. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (5) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. (6) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on April 12, 2017. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2017–07983 Filed 4–21–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2016–9266; Airspace Docket No. 16–ASO–5] Establishment of Class E Airspace; Kill Devil Hills, NC Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action establishes Class E airspace at Kill Devil Hills, NC, to accommodate new Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedures (SIAPs) serving First Flight Airport. Controlled airspace is necessary for the safety and management of instrument flight rules (IFR) operations at the airport. DATES: Effective 0901 UTC, June 22, 2017. The Director of the Federal Register approves this incorporation by reference action under title 1, Code of SUMMARY: E:\FR\FM\24APR1.SGM 24APR1

Agencies

[Federal Register Volume 82, Number 77 (Monday, April 24, 2017)]
[Rules and Regulations]
[Pages 18849-18852]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-07983]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1015; Directorate Identifier 2013-NE-37-AD;
Amendment 39-18859; AD 2017-08-10]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding airworthiness directive (AD) 2017-01-01 for
all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84,
RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-
Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2017-01-01
required inspections of the low-pressure turbine (LPT) exhaust case and
support assembly or tail bearing housing (TBH) to detect cracks or
damage. This AD corrects references to certain service bulletins in the
compliance section of AD 2017-01-01. This AD was prompted by reports
that references to service bulletins in AD 2017-01-01 are incorrect. We
are issuing this AD to correct the unsafe condition on these products.

DATES: This AD is effective May 9, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 26,
2017 (82 FR 3146, January 11, 2017).
We must receive any comments on this AD by June 8, 2017.

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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Rolls-Royce
plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ;
phone: 011-44-1332-242424; fax: 011-44-1332-245418, or email: https://www.rolls-royce.com/contact/civil_team.jsp. You may view this service
information at the FAA, Engine & Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803. For information on the availability of
this material at the FAA, call 781-238-7125. It is also available on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2013-1015.

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-2013-
1015; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the mandatory continuing airworthiness information,
regulatory evaluation, any comments received, and other information.
The address for the Docket Office (phone: 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781-
238-7199; email: robert.green@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2013-1015; Directorate Identifier 2013-NE-37-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.

Discussion

On December 22, 2016, we issued AD 2017-01-01, Amendment 39-18768
(82 FR 3146, January 11, 2017), for all RR RB211-Trent 970-84, RB211-
Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent
977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan engines.
AD 2017-01-01 required inspections of the LPT exhaust case and support
assembly or TBH to detect cracks or damage. AD 2017-01-01 resulted from
RR performing additional analysis of inspection results and determining
that the existing inspections need to be modified. We issued AD 2017-
01-01 to

[[Page 18850]]

prevent failure of the TBH, resulting in damage to the engine and to
the airplane.

Actions Since AD 2017-01-01 Was Issued

Since we issued AD 2017-01-01, we learned that certain references
to certain service bulletins in AD 2017-01-01 are incorrect. In the
fourth row, second column of Table 2 to paragraph (f) of AD 2017-01-01,
the applicable Alert Non-Modification Service Bulletin (NMSB) states
``RB.211-72-AJ101'' but the correct reference is ``RB.211-72-AH154.''
In addition, two references to ``NMSB RB.211-72-J024'' in Table 1 and
Table 2 to paragraph (f) of AD 2017-01-01 should say ``SB RB.211-72-
J024''. We have corrected those references in this AD.

Related Service Information Under 1 CFR Part 51

RR has issued Alert NMSB RB.211-72-AG971, Revision 2, dated May 5,
2016; Alert NMSB RB.211-72-AH154, Revision 5, dated May 5, 2016; Alert
NMSB RB.211-72-AJ101, dated May 5, 2016; and Service Bulletin (SB)
RB.211-72-J055, dated March 22, 2016. RR Alert NMSB RB.211-72-AG971
describes procedures for on-wing or in-shop inspection of the TBH mount
lug run-outs. RR Alert NMSB RB.211-72-AH154 describes procedures for an
on-wing or in-shop inspection of a pre-mod 72-J024 TBH. RR Alert NMSB
RB.211-72-AJ101 describes procedures for on-wing or in-shop inspection
of a post-mod 72-J024 TBH. RR SB RB.211-72-J055 describes procedures
for modifying the engine by introducing a revised TBH. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.

FAA's Determination

We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

AD Requirements

This AD requires inspections of the LPT exhaust case and support
assembly or TBH to detect cracks or damage.

FAA's Justification and Determination of the Effective Date

No domestic operators use this product. Therefore, we find that
notice and opportunity for prior public comment are unnecessary and
that good cause exists for making this amendment effective in less than
30 days.

Costs of Compliance

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

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection of the TBH............. 8 work-hours x $85 $0 $680 per inspection $0
per hour = $680. cycle.
----------------------------------------------------------------------------------------------------------------

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.
We are 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,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends part 39 of the Federal Aviation
Regulations (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 removing airworthiness directive (AD)
2017-01-01, Amendment 39-18768 (82 FR 3146, January 11, 2017), and
adding the following new AD:

2017-08-10 Rolls-Royce plc: Amendment 39-18859; Docket No. FAA-2013-
1015; Directorate Identifier 2013-NE-37-AD.

(a) Effective Date

This AD is effective May 9, 2017.

(b) Affected ADs

This AD replaces AD 2017-01-01, Amendment 39-18768 (82 FR 3146,
January 11, 2017).

This AD applies to all Rolls-Royce plc (RR) RB211-Trent 970-84,
RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-
Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan
engines.

(d) Subject

Joint Aircraft System Component (JASC) Code 7200, Engine
(Turbine/Turboprop).

[[Page 18851]]

(e) Unsafe Condition

This AD was prompted by reports that references to certain
service bulletins are incorrect. We are issuing this AD to prevent
failure of the tail bearing housing (TBH), resulting in damage to
the engine and to the airplane.

(f) Compliance

Comply with this AD within the compliance times specified,
unless already done.
(1) Within the compliance times and using the service
information specified in Table 1 to paragraph (f) of this AD,
accomplish on-wing inspections of the TBH features using the
following instructions, as applicable.
(i) If during any on-wing inspection of the TBH mount lug run-
outs done using the Accomplishment Instructions, paragraph 3.A.(1),
of RR Alert Non-Modification Service Bulletin (NMSB) RB.211-72-
AG971, Revision 2, dated May 5, 2016, any cracks less than or equal
to 2 mm in length are found, remove the engine from service within
10 flight cycles (FCs). If any cracks greater than 2 mm are found,
remove the engine from service before further flight.
(ii) If during any on-wing inspection of the TBH mount lug run-
outs done using the Accomplishment Instructions, paragraph 3.A.(2),
of RR Alert NMSB RB.211-72-AG971, Revision 2, dated May 5, 2016, any
crack indications resulting in an inspection signal with an
amplitude of 50% full screen height or more are found, remove the
engine from service before further flight.
(iii) If during any on-wing inspection of a pre-mod 72-J024 TBH,
any crack or damage is found on the TBH mount lug forging leading
edge (LE) areas, re-inspect the engine or remove the engine from
service in accordance with the Accomplishment Instructions,
paragraph 3.A.(3)(t), of RR Alert NMSB RB.211-72-AH154, Revision 5,
dated May 5, 2016.
(iv) If during any on-wing inspection of a post-mod 72-J024 TBH,
any crack is found on the TBH mount lug forging LE or cutback areas,
re-inspect the engine or remove the engine from service in
accordance with the Accomplishment Instructions, paragraph
3.A.(3)(t), of RR Alert NMSB RB.211-72-AJ101, dated May 5, 2016.
(2) Within the compliance times and using the service
information specified in Table 2 to paragraph (f) of this AD,
perform in-shop inspections of the TBH features using the following
instructions, as applicable.
(i) If during any in-shop inspection of the TBH, any crack is
found on the TBH mount lug or central male catcher run-outs, replace
the TBH with a TBH eligible for installation before the engine is
returned to service.
(ii) If during any in-shop inspection of the TBH, any crack is
found on the top core vanes, reject as unserviceable or repair the
TBH in accordance with the Accomplishment Instructions, paragraph
3.C.(1)(f), of RR Alert NMSB RB.211-72-AG971 Revision 2, dated May
5, 2016, before the engine is returned to service.
(iii) If during any in-shop inspection of a pre-mod 72-J024 TBH,
any crack or damage is found on the TBH mount lug forging LE areas,
reject as unserviceable or repair the TBH in accordance with the
Accomplishment Instructions, paragraph 3.B.(2)(u)(ii), of RR Alert
NMSB RB.211-72-AH154, Revision 5, dated May 5, 2016, or the
Accomplishment Instructions, paragraph 3.C.(1)(f), of RR Alert NMSB
RB.211-72-AG971, Revision 2, dated May 5, 2016, before the engine is
returned to service.
(iv) If during any in-shop inspection of a post-mod 72-J024 TBH,
any crack is found on the TBH mount lug forging LE or cutback areas,
repair the TBH in accordance with the Accomplishment Instructions,
paragraph 3.B.(2)(u)(ii), of RR Alert NMSB RB.211-72-AJ101, dated
May 5, 2016, or the Accomplishment Instructions, paragraph
3.C.(1)(f), of Alert NMSB RB.211-72-AG971, Revision 2, dated May 5,
2016, before the engine is returned to service.

Table 1 to Paragraph (f)--TBH On-Wing Inspections
----------------------------------------------------------------------------------------------------------------
Alternate NMSB
Applicable NMSB instructions Repeat inspection
Affected TBH P/N and feature and paragragph acceptable for Initial inspection interval (not to
prior compliance exceed)
----------------------------------------------------------------------------------------------------------------
All--Mount Lug Run-outs........ RB.211-72-AG971, In-shop: RB.211-72- Before exceeding 2,200 FCs.
Revision 2, AG971, Revision 2,200 FCs since
Paragraph 3.A. 2, Paragraph 3.B new.
or 3.C.
Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AH154, In-shop: RB.211-72- Before exceeding 1,000 FCs.
Forging LE Areas--for a TBH Revision 5, AH154, Revision 1,000 FCs since
that has not exceeded 900 FCs Paragraph 3.A. 5, Paragraph new.
since new on April 7, 2014. 3.B., or
RB.211[dash]72-AG
971, Revision 2,
Paragraph 3.C.
Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AH154, In-shop: RB.211-72- Within 100 FCs 1,000 FCs.
Forging LE Areas--for a TBH Revision 5, AH154, Revision after April 7,
that has exceeded 900 FCs Paragraph 3.A. 5, Paragraph 2014.
since new on April 7, 2014. 3.B., or
RB.211[dash]72-AG
971, Revision 2,
Paragraph 3.C.
Post-mod 72-J024 TBH--Mount Lug RB.211-72-AJ101, In-shop: RB.211-72- Before exceeding 1,000 FCs.
Forging LE and Cutback Areas. Paragraph 3.A. AG971, Revison 2, 1,000 FCs since
Paragraph 3.C, or SB
RB.211-72-AJ101, RB.211[dash]72[da
Paragraph 3.B. sh]J024
embodiment.
----------------------------------------------------------------------------------------------------------------

Table 2 to Paragraph (f)--TBH In-Shop Inspections
----------------------------------------------------------------------------------------------------------------
Alternate NMSB
Applicable NMSB instructions Repeat inspection
Affected TBH P/N and feature and paragraph acceptable for Initial inspection interval (not to
prior compliance exceed)
----------------------------------------------------------------------------------------------------------------
All--Mount Lug Run-outs........ RB.211-72-AG971, On-wing: RB.211-72- Before exceeding 2,200 FCs.
Revision 2, AG971, Revision 2,200 flight FCs
Paragraph 3. 2, Paragraph since new.
3.A., or
In-shop: RB.211-72-
AG971, Revision
2, Paragraph 3.C.
All--Top Core Vanes and Central RB.211-72-AG971, None.............. Before exceeding 3,800 FCs.
Male Catcher Run[dash]outs. Revision 2, 3,800 FCs since
Paragraph 3.C. new.

[[Page 18852]]

Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AH154, On-wing: RB.211-72- Before exceeding 1,000 FCs.
Forging LE Areas--for a TBH Revision 5, AH154, Revision 1,000 FCs since
that has not exceeded 900 FCs Paragraph 3.B. 5, Section 3.A, new.
since new on April 7, 2014. or
In-shop: RB.211-72-
AG971, Revision
2, Paragraph 3.C.
Pre-mod 72-J024 TBH--Mount Lug RB.211-72-AH154, On-wing: RB.211-72- Within 100 FCs 1,000 FCs.
Forging LE Areas--for a TBH Revision 5, AH154, Revision after the
that has exceeded 900 FCs Paragraph 3.B. 5, Section 3.A, effective date of
since new on April 7, 2014. or this AD.
In-shop: RB.211-72-
AG971, Revision
2, Paragraph 3.C.
Post-mod 72-J024 TBH--Mount Lug RB.211-72-AJ101, On-wing: RB.211-72- Before exceeding 1,000 FCs.
Forging LE and Cutback Areas. Paragraph 3.B. AJ101, Section 1,000 FCs since
3.A, or SB RB.211[dash]72-
In-shop: RB.211-72- J024 embodiment.
AG971, Revision
2, Paragraph 3.C.
----------------------------------------------------------------------------------------------------------------

(g) Credit for Previous Actions

(1) If you performed inspections and corrective actions on an
engine before the effective date of this AD, in accordance with
earlier versions of RR Alert NMSB RB.211-72-AG971, Revision 2, dated
May 5, 2016, or RR Alert NMSB RB.211-72-AH154, Revision 5, dated May
5, 2016, you met the requirements of paragraph (f)(1) or (2) of this
AD, as applicable.
(2) If, on or before April 7, 2014, you performed the
inspections and corrective actions required by paragraphs (f)(1) and
(2) of this AD using RR Technical Variance (TV) No. 124801, Issue 2,
dated July 4, 2012 or earlier versions; or RR TV No. 124851, Issue
2, dated July 4, 2012 or earlier versions; you met the requirements
for a mount lug run-out inspection.
(3) If, on or before April 7, 2014, you performed the
inspections and corrective actions required by paragraphs (f)(1) and
(2) of this AD using RR Repeater TV No. 132043, Issue 1, dated March
25, 2013 or earlier versions; or using RR Repeater TV No. 132217,
Issue 5, dated May 23, 2013 or earlier versions; you met the
requirements for the mount lug forging LE inspections of this AD.

(h) Optional Terminating Action

(1) Accomplishment of corrective actions required by paragraphs
(f)(1) and (2) of this AD does not constitute terminating action for
the repetitive inspections required by this AD.
(2) Modification of an engine in accordance with the
instructions of RR Service Bulletin RB.211-72-J055, dated March 22,
2016, constitutes terminating action for the repetitive inspections
required by paragraphs (f)(1) and (2) of this AD for that engine,
provided that, following this modification, no affected TBH is
installed on that engine.

(i) Alternative Methods of Compliance (AMOCs)

The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: ANE-AD-AMOC@faa.gov.

(j) Related Information

(1) For more information about this AD, contact Robert Green,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803;
phone: 781-238-7754; fax: 781-238-7199; email: robert.green@faa.gov.
(2) Refer to MCAI European Aviation Safety Agency AD 2016-0193,
dated September 30, 2016, for more information. You may examine the
MCAI in the AD docket on the Internet at https://www.regulations.gov
by searching for and locating it in Docket No. FAA-2013-1015.
(3) RR TV No. 124801, Issue 2, dated July 4, 2012; RR TV No.
124851, Issue 2, dated July 4, 2012, Repeater TV No. 132043, Issue
1, dated March 25, 2013, and Repeater TV No. 132217, Issue 5, dated
May 23, 2013; which are not incorporated by reference in this AD,
can be obtained from RR using the contact information in paragraph
(k)(3) of this AD.

(k) Material Incorporated by Reference

(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
January 26, 2017 (82 FR 3146, January 11, 2017).
(i) Rolls-Royce plc (RR) Service Bulletin RB.211-72-J055, dated
March 22, 2016.
(ii) RR Alert Non-Modification Service Bulletin (NMSB) RB.211-
72-AJ101, dated May 5, 2016;
(iii) RR Alert NMSB RB.211-72-AG971, Revision 2, dated May 5,
2016; and
(iv) RR Alert NMSB RB.211-72-AH154, Revision 5, dated May 5,
2016.
(4) For RR service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby,
England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-
245418, or email: https://www.rolls-royce.com/contact/civil_team.jsp.
(5) You may view this service information at FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803.
For information on the availability of this material at the FAA,
call 781-238-7125.
(6) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in Burlington, Massachusetts, on April 12, 2017.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2017-07983 Filed 4-21-17; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.