Airworthiness Directives; General Electric Company Turbofan Engines, 53976-53979 [2018-23466]

Download as PDF Federal Register / Vol. 83, No. 208 / Friday, October 26, 2018 / Rules and Regulations (g) Required Actions (1) For combustion cases listed in Planning Information, Table 1, paragraph 1.A. of GE SB GE90–100 S/B 72–0788, Revision 4, dated July 30, 2018, except combustion cases with S/Ns FDBK3717, FDBK3872, or FDBK4849, remove the affected cases from service, using the cycles specified in Table 1 to paragraph (g) of this AD. (2) For combustion cases with S/Ns listed in Table 3, paragraph 1.C., Planning Information, of GE SB GE90–100 S/B 72– 0788, Revision 4, dated July 30, 2018, remove the affected cases from service before exceeding the Maximum In-Service CSN listed in Table 3, of GE SB GE90–100 S/B 72– 0788, Revision 4, dated July 30, 2018. (3) For combustion cases with S/Ns listed in paragraph 1.A., Planning Information, of GE SB GE90–100 SB 72–0784 R00, dated May 4, 2018, remove the affected cases from service within 10 cycles in service from the effective date of this AD. (4) For combustion cases with S/Ns listed in Table 1, paragraph 1.A., Planning Information, of GE SB GE90–100 SB 72–0793 R00, dated August 10, 2018, remove the affected cases from service at the next engine shop visit. (5) Replace the removed combustion case with a part eligible for installation before further flight. or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. 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. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (h) Definitions (1) For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation of the engine, without subsequent engine maintenance, does not constitute an engine shop visit. (2) For the purpose of this AD, a ‘‘part eligible for installation’’ is any combustion case not identified in paragraph (c)(1) of this AD or a combustion case listed in this AD that has been inspected and repaired by a method approved by the Manager, ECO Branch, FAA. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector VerDate Sep<11>2014 18:06 Oct 25, 2018 Jkt 247001 (j) Related Information For more information about this AD, contact Matthew Smith, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7735; fax: 781–238–7199; email: matthew.c.smith@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) General Electric Company (GE) GE90– 100 Service Bulletin (SB) SB 72–0784 R00, dated May 4, 2018. (ii) GE SB GE90–100 S/B 72–0788, Revision 4, dated July 30, 2018. (iii) GE SB GE90–100 SB 72–0793 R00, dated August 10, 2018. (3) For service information identified in this AD, contact General Electric Company, GE Aviation, 1 Neumann Way, Cincinnati, OH 45215; telephone 513–552–3272; email: aviation.fleetsupport@ge.com. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Issued in Burlington, Massachusetts, on October 18, 2018. Karen M. Grant, Acting Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–23468 Filed 10–25–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0406; Product Identifier 2013–NE–30–AD; Amendment 39– 19457; AD 2018–20–23] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2017–07– 04 for General Electric Company (GE) GE90–110B1 and GE90–115B turbofan engines with certain high-pressure compressor (HPC) rotor stage 2–5 spools installed. AD 2017–07–04 required removing certain HPC rotor stage 2–5 spools from service at times determined by a drawdown plan. This AD requires SUMMARY: E:\FR\FM\26OCR1.SGM 26OCR1 ER26OC18.001</GPH> khammond on DSK30JT082PROD with RULES 53976 Federal Register / Vol. 83, No. 208 / Friday, October 26, 2018 / Rules and Regulations removing certain HPC rotor stage 2–5 spools from service before reaching the new reduced life limit and replacing them with parts eligible for installation. This AD was prompted by the publication of a GE service bulletin (SB) that increases the number of affected HPC rotor stage 2–5 spools and includes HPC rotor stage 2–5 spools that were inadvertently omitted from the applicability of AD 2017–07–04. We are issuing this AD to address the unsafe condition on these products. This AD is effective November 30, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 30, 2018. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 21, 2017 (82 FR 16728, April 6, 2017). DATES: For service information identified in this final rule, contact General Electric Company, 1 Neumann Way, Room 285, Cincinnati, OH 45215; phone: 513–552–3272; email: geae.aoc@ ge.com. You may view this service information at the FAA, Engine and Propeller Standards 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 on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0406. ADDRESSES: Examining the AD Docket khammond on DSK30JT082PROD with RULES You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0406; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) 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 Bethka, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7129; fax: 781–238–7199; email: david.bethka@faa.gov. SUPPLEMENTARY INFORMATION: VerDate Sep<11>2014 18:06 Oct 25, 2018 Jkt 247001 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2017–07–04, Amendment 39–18842 (82 FR 16728, April 6, 2017), (‘‘AD 2017–07–04’’). AD 2017–07–04 applied to GE GE90–110B1 and GE90–115B turbofan engines with certain HPC rotor stage 2–5 spools installed. The NPRM published in the Federal Register on June 25, 2018 (83 FR 29474). The NPRM was prompted by the publication of a GE SB that increases the number of affected HPC rotor stage 2–5 spools and includes HPC rotor stage 2–5 spools that were inadvertently omitted from the applicability of AD 2017–07–04. The NPRM proposed to require removing certain HPC rotor stage 2–5 spools from service before reaching the new reduced life limit and replacing them with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To List Additional Service Information in Required Actions All Nippon Airways (ANA), Azur Aviation, and Lufthansa Technik AG (Lufthansa) questioned why HPC rotor stage 2–5 spools listed in paragraph (c) of this AD, identified in GE SB GE90– 100 SB 72–0499 R01, dated February 5, 2014, are not required to be replaced in paragraph (g) of this AD. Lufthansa reasoned that GE SB GE90–100 SB 72– 0499 R01, dated February 5, 2014, requires replacement of affected spools, but this AD does not. We disagree. Based on information provided by GE, and to the best of our knowledge, all HPC rotor stage 2–5 spools listed in paragraph 1.A. of GE SB GE90–100 SB 72–0499 R01, dated February 5, 2014, have been removed from service. Because these HPC rotor stage 2–5 spools have been removed from service, we did not require their removal under paragraph (g) of this AD. This AD, however, includes an installation prohibition under paragraph (h) to prevent installation of these HPC rotor stage 2–5 spools. We did not change this AD. Request To Consider a Threshold Rework Option FedEx Express (FedEx) requested that certain HPC rotor stage 2–5 spools be considered for a potential GE rework option to extend their life beyond PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 53977 allowances of this AD, before removal from service. FedEx reasoned that GE intends to provide a rework option that will extend the life of HPC rotor stage 2–5 spools that are removed before reaching 4,500 cycles. This rework option could extend the on-wing times for some engines. We disagree. While GE intends to provide a rework option to extend the life of certain HPC rotor stage 2–5 spools, we do not require compliance based on information that has not yet been published. We based the compliance on the most recently published service information. This AD and the associated GE service information do not allow credit for rework or life extensions. We did not change this AD. Request To Verify Applicability and Purpose ANA requested clarification regarding whether the proposed AD intends to require removing the following three (3) HPC rotor stage 2–5 spool configurations from service at a time determined by this AD: (1) HPC rotor stage 2–5 spools that use the original seal teeth coating. (Known as Population-1); (2) HPC rotor stage 2–5 spools that use the modified seal teeth coating. (Known as Population-2); and (3) HPC rotor stage 2–5 spools that use the modified seal teeth coating without inner-teeth coating. (Known as Population-3). We interpret ANA’s comment as request to verify if this AD requires removal of the HPC rotor stage 2–5 spools identified in GE SB GE90–100 SB 72–0499 R01, dated February 5, 2014; GE SB GE90–100 SB 72–0659 R01, dated February 18, 2016; and GE SB GE90–100 S/B 72–0714, Revision 01, dated February 16, 2018. ANA commented that requirements and actions in this AD are difficult to understand. The purpose of this AD is to remove the HPC rotor stage 2–5 spools identified in GE SB GE90–100 SB 72– 0659 R01, dated February 18, 2016, and GE SB GE90–100 S/B 72–0714, Revision 01, dated February 16, 2018, from service, and to prohibit the installation of those HPC rotor stage 2–5 spools and the HPC rotor stage 2–5 spools identified in GE SB GE90–100 SB 72– 0499 R01, dated February 5, 2014. Paragraphs (c) and (g) of this AD list the affected part numbers and serial numbers. We did not change this AD. Support for the AD The Air Line Pilots Association, Boeing Company, and American E:\FR\FM\26OCR1.SGM 26OCR1 53978 Federal Register / Vol. 83, No. 208 / Friday, October 26, 2018 / Rules and Regulations Airlines expressed support for the NPRM as written. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed GE SB GE90–100 SB 72– 0499 R01, dated February 5, 2014; GE SB GE90–100 SB 72–0659 R01, dated February 18, 2016; and GE SB GE90–100 S/B 72–0714, Revision 01, dated February 16, 2018. GE SB GE90–100 SB 72–0499 R01 describes procedures for identification and removal from service of HPC rotor stage 2–5 spools that use the original seal tooth coating process. GE SB GE90– 100 SB 72–0659 R01 describes procedures for identification and removal from service of HPC rotor stage 2–5 spools that use a modified seal tooth coating process. GE SB GE90–100 S/B 72–0714, Revision 01 describes procedures for identification and removal from service of HPC rotor stage 2–5 spools that use the modified seal tooth coating process, without coating between the seal teeth. 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. Costs of Compliance We estimate that this AD affects 85 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: khammond on DSK30JT082PROD with RULES ESTIMATED COSTS Action Labor cost Parts cost Paragraph (g)(1) Spools Replacement ........... Paragraph (g)(2) Spools Replacement ........... 0 work-hours × $85 per hour = $0 ................. 0 work-hours × $85 per hour = $0 ................. Regulatory Findings 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) 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, 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. 18:06 Oct 25, 2018 Jkt 247001 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 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES Frm 00014 Fmt 4700 $5,054,214 2,460,024 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2017–07–04, Amendment 39–18842 (82 FR 16728, April 6, 2017), and adding the following new AD: ■ 2018–20–23 General Electric Company: Amendment 39–19457; Docket No. FAA–2018–0406; Product Identifier 2013–NE–30–AD. (a) Effective Date This AD is effective November 30, 2018. (b) Affected ADs This AD replaces AD 2017–07–04, Amendment 39–18842 (82 FR 16728, April 6, 2017). (c) Applicability This AD applies to General Electric Company (GE) GE90–110B1 and GE90–115B turbofan engines with HPC rotor stage 2–5 spools, with: (1) A serial number (S/N) listed in either, paragraph 4, Appendix A of GE Service Bulletin (SB) No. GE90–100 SB 72–0499 R01, dated February 5, 2014; in paragraph 4, Appendix A of GE SB GE90–100 SB 72–0659 R01, dated February 18, 2016; or in paragraph 4, Appendix A, of GE SB GE90– 100 S/B 72–0714, Revision 01, dated February 16, 2018. (2) A part number (P/N) 351–103–109–0, P/ N 351–103–110–0, P/N 351–103–147–0 or P/ N 351–103–152–0, with any S/N. (d) Subject 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 $229,737 39,048 Cost on U.S. operators Authority: 49 U.S.C. 106(g), 40113, 44701. Authority for This Rulemaking VerDate Sep<11>2014 $229,737 39,048 Cost per product Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. E:\FR\FM\26OCR1.SGM 26OCR1 Federal Register / Vol. 83, No. 208 / Friday, October 26, 2018 / Rules and Regulations (e) Unsafe Condition This AD was prompted by reports of cracks in HPC rotor stage 2–5 spool aft spacer arms. We are issuing this AD to prevent failure of the HPC rotor stage 2–5 spools. The unsafe condition, if not addressed, could result in uncontained spool release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. khammond on DSK30JT082PROD with RULES (g) Required Actions (1) Remove from service HPC rotor stage 2– 5 spools with S/Ns listed in paragraph 4, Appendix A, of GE SB GE90–100 SB 72–0659 R01, dated February 18, 2016, as follows, or before further flight, whichever occurs later: (i) For spools with fewer than 4,500 flight cycles since new (CSN) as of April 21, 2017, remove before exceeding 5,000 CSN. (ii) For spools with 4,500 CSN or more but fewer than 5,200 CSN as of April 21, 2017, remove within 500 CIS but not to exceed 5,500 CSN. (iii) For spools with 5,200 CSN or more but fewer than 5,600 CSN as of April 21, 2017, remove within 300 CIS but not to exceed 5,800 CSN. (iv) For spools with 5,600 CSN or more but fewer than 5,800 CSN as of April 21, 2017, remove within 200 CIS but not to exceed 5,850 CSN. (v) For spools with 5,800 CSN or more but fewer than 6,000 CSN as of April 21, 2017, remove within 50 CIS but not to exceed 6,000 CSN. (vi) For spools with 6,000 CSN or more as of April 21, 2017, remove before the next flight. (2) Remove from service HPC rotor stage 2– 5 spools listed in paragraph (c)(2) of this AD and HPC rotor stage 2–5 spools with S/Ns listed in paragraph 4, Appendix A, of GE SB GE90–100 S/B 72–0714, Revision 01, dated February 16, 2018, before exceeding 8,200 CSN, or before further flight, whichever occurs later. (h) Installation Prohibition (1) After the effective date of this AD, do not install or reinstall onto any engine, any HPC rotor stage 2–5 spool with an S/N listed in paragraph 4, Appendix A, of GE SB No. GE90–100 SB 72–0499 R01, dated February 5, 2014, or paragraph 4, Appendix A, of GE SB GE90–100 SB72–0659 R01, dated February 18, 2016, that exceeds 5,000 CSN. (2) After the effective date of this AD, do not install or reinstall onto any engine, any HPC rotor stage 2–5 spool listed in paragraph (c)(2) of this AD, or HPC rotor stage 2–5 spool with an S/N listed in paragraph 4, Appendix A, of GE SB GE90–100 S/B 72–0714, Revision 01, dated February 16, 2018, that exceeds 8,200 CSN. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector VerDate Sep<11>2014 18:06 Oct 25, 2018 Jkt 247001 53979 or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. 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. DEPARTMENT OF TRANSPORTATION (j) Related Information AGENCY: For more information about this AD, contact David Bethka, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7129; fax: 781–238–7199; email: david.bethka@faa.gov. SUMMARY: (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 November 30, 2018. (i) General Electric Company (GE) Service Bulletin (SB) GE90–100 SB 72–0499 R01, dated February 5, 2014. (ii) GE SB GE90–100 S/B 72–0714, Revision 01, dated February 16, 2018. (4) The following service information was approved for IBR on April 21, 2017 (82 FR 16728, April 6, 2017). (i) GE SB GE90–100 SB 72–0659 R01, dated February 18, 2016. (ii) [Reserved.] (5) For service information identified in this AD, contact General Electric Company, 1 Neumann Way, Room 285, Cincinnati, OH 45215; phone: 513–552–3272; email: geae.aoc@ge.com. (6) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. (7) 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on October 17, 2018. Karen M. Grant, Acting Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–23466 Filed 10–25–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2018–0094; Airspace Docket No. 18–ASW–4] RIN 2120–AA66 Amendment of Class D Airspace; Tulsa, OK Federal Aviation Administration (FAA), DOT. ACTION: Final rule. This action amends Class D airspace designated as an extension at Tulsa Lloyd Jones Jr. Airport, Tulsa, OK. This action is a result of an airspace review caused by the decommissioning of the Glenpool VHF omnidirectional range (VOR) navigation aid as part of the VOR Minimum Operational Newtork (MON) Program and the cancellation of the associated instrument procedures. The geographic coordinates of the airport are also updated; to coincide with the FAA’s aeronautical database, as well as an editorial change removing the city associated with the airport name in the airspace legal description. Also, the outdated term ‘‘Airport/Facility Directory’’ is replaced with ‘‘Chart Supplement’’. DATES: Effective 0901 UTC, January 3, 2019. The Director of the Federal Register approves this incorporation by reference action under Title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.11 and publication of conforming amendments. ADDRESSES: FAA Order 7400.11C, Airspace Designations and Reporting Points, and subsequent amendments can be viewed online at http://www.faa.gov/ air_traffic/publications/. For further information, you can contact the Airspace Policy Group, Federal Aviation Administration, 800 Independence Avenue SW, Washington, DC 20591; telephone: (202) 267–8783. The Order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of FAA Order 7400.11C at NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal-register/cfr/ ibr-locations.html. FAA Order 7400.11, Airspace Designations and Reporting Points, is published yearly and effective on September 15. FOR FURTHER INFORMATION CONTACT: Rebecca Shelby, Federal Aviation Administration, Operations Support E:\FR\FM\26OCR1.SGM 26OCR1

Agencies

[Federal Register Volume 83, Number 208 (Friday, October 26, 2018)]
[Rules and Regulations]
[Pages 53976-53979]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23466]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0406; Product Identifier 2013-NE-30-AD; Amendment 
39-19457; AD 2018-20-23]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2017-07-04 for 
General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines 
with certain high-pressure compressor (HPC) rotor stage 2-5 spools 
installed. AD 2017-07-04 required removing certain HPC rotor stage 2-5 
spools from service at times determined by a drawdown plan. This AD 
requires

[[Page 53977]]

removing certain HPC rotor stage 2-5 spools from service before 
reaching the new reduced life limit and replacing them with parts 
eligible for installation. This AD was prompted by the publication of a 
GE service bulletin (SB) that increases the number of affected HPC 
rotor stage 2-5 spools and includes HPC rotor stage 2-5 spools that 
were inadvertently omitted from the applicability of AD 2017-07-04. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective November 30, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 30, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of April 
21, 2017 (82 FR 16728, April 6, 2017).

ADDRESSES: For service information identified in this final rule, 
contact General Electric Company, 1 Neumann Way, Room 285, Cincinnati, 
OH 45215; phone: 513-552-3272; email: [email protected]. You may view 
this service information at the FAA, Engine and Propeller Standards 
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 on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2018-0406.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0406; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) 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 Bethka, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7129; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2017-07-04, Amendment 39-18842 (82 FR 16728, 
April 6, 2017), (``AD 2017-07-04''). AD 2017-07-04 applied to GE GE90-
110B1 and GE90-115B turbofan engines with certain HPC rotor stage 2-5 
spools installed. The NPRM published in the Federal Register on June 
25, 2018 (83 FR 29474). The NPRM was prompted by the publication of a 
GE SB that increases the number of affected HPC rotor stage 2-5 spools 
and includes HPC rotor stage 2-5 spools that were inadvertently omitted 
from the applicability of AD 2017-07-04. The NPRM proposed to require 
removing certain HPC rotor stage 2-5 spools from service before 
reaching the new reduced life limit and replacing them with parts 
eligible for installation. We are issuing this AD to address the unsafe 
condition on these products.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To List Additional Service Information in Required Actions

    All Nippon Airways (ANA), Azur Aviation, and Lufthansa Technik AG 
(Lufthansa) questioned why HPC rotor stage 2-5 spools listed in 
paragraph (c) of this AD, identified in GE SB GE90-100 SB 72-0499 R01, 
dated February 5, 2014, are not required to be replaced in paragraph 
(g) of this AD. Lufthansa reasoned that GE SB GE90-100 SB 72-0499 R01, 
dated February 5, 2014, requires replacement of affected spools, but 
this AD does not.
    We disagree. Based on information provided by GE, and to the best 
of our knowledge, all HPC rotor stage 2-5 spools listed in paragraph 
1.A. of GE SB GE90-100 SB 72-0499 R01, dated February 5, 2014, have 
been removed from service. Because these HPC rotor stage 2-5 spools 
have been removed from service, we did not require their removal under 
paragraph (g) of this AD. This AD, however, includes an installation 
prohibition under paragraph (h) to prevent installation of these HPC 
rotor stage 2-5 spools. We did not change this AD.

Request To Consider a Threshold Rework Option

    FedEx Express (FedEx) requested that certain HPC rotor stage 2-5 
spools be considered for a potential GE rework option to extend their 
life beyond allowances of this AD, before removal from service. FedEx 
reasoned that GE intends to provide a rework option that will extend 
the life of HPC rotor stage 2-5 spools that are removed before reaching 
4,500 cycles. This rework option could extend the on-wing times for 
some engines.
    We disagree. While GE intends to provide a rework option to extend 
the life of certain HPC rotor stage 2-5 spools, we do not require 
compliance based on information that has not yet been published. We 
based the compliance on the most recently published service 
information. This AD and the associated GE service information do not 
allow credit for rework or life extensions. We did not change this AD.

Request To Verify Applicability and Purpose

    ANA requested clarification regarding whether the proposed AD 
intends to require removing the following three (3) HPC rotor stage 2-5 
spool configurations from service at a time determined by this AD:
    (1) HPC rotor stage 2-5 spools that use the original seal teeth 
coating. (Known as Population-1);
    (2) HPC rotor stage 2-5 spools that use the modified seal teeth 
coating. (Known as Population-2); and
    (3) HPC rotor stage 2-5 spools that use the modified seal teeth 
coating without inner-teeth coating. (Known as Population-3).
    We interpret ANA's comment as request to verify if this AD requires 
removal of the HPC rotor stage 2-5 spools identified in GE SB GE90-100 
SB 72-0499 R01, dated February 5, 2014; GE SB GE90-100 SB 72-0659 R01, 
dated February 18, 2016; and GE SB GE90-100 S/B 72-0714, Revision 01, 
dated February 16, 2018. ANA commented that requirements and actions in 
this AD are difficult to understand.
    The purpose of this AD is to remove the HPC rotor stage 2-5 spools 
identified in GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016, 
and GE SB GE90-100 S/B 72-0714, Revision 01, dated February 16, 2018, 
from service, and to prohibit the installation of those HPC rotor stage 
2-5 spools and the HPC rotor stage 2-5 spools identified in GE SB GE90-
100 SB 72-0499 R01, dated February 5, 2014. Paragraphs (c) and (g) of 
this AD list the affected part numbers and serial numbers. We did not 
change this AD.

Support for the AD

    The Air Line Pilots Association, Boeing Company, and American

[[Page 53978]]

Airlines expressed support for the NPRM as written.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed GE SB GE90-100 SB 72-0499 R01, dated February 5, 2014; 
GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016; and GE SB GE90-
100 S/B 72-0714, Revision 01, dated February 16, 2018.
    GE SB GE90-100 SB 72-0499 R01 describes procedures for 
identification and removal from service of HPC rotor stage 2-5 spools 
that use the original seal tooth coating process. GE SB GE90-100 SB 72-
0659 R01 describes procedures for identification and removal from 
service of HPC rotor stage 2-5 spools that use a modified seal tooth 
coating process. GE SB GE90-100 S/B 72-0714, Revision 01 describes 
procedures for identification and removal from service of HPC rotor 
stage 2-5 spools that use the modified seal tooth coating process, 
without coating between the seal teeth.
    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.

Costs of Compliance

    We estimate that this AD affects 85 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Paragraph (g)(1) Spools Replacement...  0 work-hours x $85 per          $229,737        $229,737      $5,054,214
                                         hour = $0.
Paragraph (g)(2) Spools Replacement...  0 work-hours x $85 per            39,048          39,048       2,460,024
                                         hour = $0.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) 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, 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 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) 
2017-07-04, Amendment 39-18842 (82 FR 16728, April 6, 2017), and adding 
the following new AD:

2018-20-23 General Electric Company: Amendment 39-19457; Docket No. 
FAA-2018-0406; Product Identifier 2013-NE-30-AD.

(a) Effective Date

    This AD is effective November 30, 2018.

(b) Affected ADs

    This AD replaces AD 2017-07-04, Amendment 39-18842 (82 FR 16728, 
April 6, 2017).

(c) Applicability

    This AD applies to General Electric Company (GE) GE90-110B1 and 
GE90-115B turbofan engines with HPC rotor stage 2-5 spools, with:
    (1) A serial number (S/N) listed in either, paragraph 4, 
Appendix A of GE Service Bulletin (SB) No. GE90-100 SB 72-0499 R01, 
dated February 5, 2014; in paragraph 4, Appendix A of GE SB GE90-100 
SB 72-0659 R01, dated February 18, 2016; or in paragraph 4, Appendix 
A, of GE SB GE90-100 S/B 72-0714, Revision 01, dated February 16, 
2018.
    (2) A part number (P/N) 351-103-109-0, P/N 351-103-110-0, P/N 
351-103-147-0 or P/N 351-103-152-0, with any S/N.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section.

[[Page 53979]]

(e) Unsafe Condition

    This AD was prompted by reports of cracks in HPC rotor stage 2-5 
spool aft spacer arms. We are issuing this AD to prevent failure of 
the HPC rotor stage 2-5 spools. The unsafe condition, if not 
addressed, could result in uncontained spool release, damage to the 
engine, and damage to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) Remove from service HPC rotor stage 2-5 spools with S/Ns 
listed in paragraph 4, Appendix A, of GE SB GE90-100 SB 72-0659 R01, 
dated February 18, 2016, as follows, or before further flight, 
whichever occurs later:
    (i) For spools with fewer than 4,500 flight cycles since new 
(CSN) as of April 21, 2017, remove before exceeding 5,000 CSN.
    (ii) For spools with 4,500 CSN or more but fewer than 5,200 CSN 
as of April 21, 2017, remove within 500 CIS but not to exceed 5,500 
CSN.
    (iii) For spools with 5,200 CSN or more but fewer than 5,600 CSN 
as of April 21, 2017, remove within 300 CIS but not to exceed 5,800 
CSN.
    (iv) For spools with 5,600 CSN or more but fewer than 5,800 CSN 
as of April 21, 2017, remove within 200 CIS but not to exceed 5,850 
CSN.
    (v) For spools with 5,800 CSN or more but fewer than 6,000 CSN 
as of April 21, 2017, remove within 50 CIS but not to exceed 6,000 
CSN.
    (vi) For spools with 6,000 CSN or more as of April 21, 2017, 
remove before the next flight.
    (2) Remove from service HPC rotor stage 2-5 spools listed in 
paragraph (c)(2) of this AD and HPC rotor stage 2-5 spools with S/Ns 
listed in paragraph 4, Appendix A, of GE SB GE90-100 S/B 72-0714, 
Revision 01, dated February 16, 2018, before exceeding 8,200 CSN, or 
before further flight, whichever occurs later.

(h) Installation Prohibition

    (1) After the effective date of this AD, do not install or 
reinstall onto any engine, any HPC rotor stage 2-5 spool with an S/N 
listed in paragraph 4, Appendix A, of GE SB No. GE90-100 SB 72-0499 
R01, dated February 5, 2014, or paragraph 4, Appendix A, of GE SB 
GE90-100 SB72-0659 R01, dated February 18, 2016, that exceeds 5,000 
CSN.
    (2) After the effective date of this AD, do not install or 
reinstall onto any engine, any HPC rotor stage 2-5 spool listed in 
paragraph (c)(2) of this AD, or HPC rotor stage 2-5 spool with an S/
N listed in paragraph 4, Appendix A, of GE SB GE90-100 S/B 72-0714, 
Revision 01, dated February 16, 2018, that exceeds 8,200 CSN.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
certification office, send it to the attention of the person 
identified in paragraph (j) of this AD. You may email your request 
to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    For more information about this AD, contact David Bethka, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7129; fax: 781-238-7199; email: 
[email protected].

(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 
November 30, 2018.
    (i) General Electric Company (GE) Service Bulletin (SB) GE90-100 
SB 72-0499 R01, dated February 5, 2014.
    (ii) GE SB GE90-100 S/B 72-0714, Revision 01, dated February 16, 
2018.
    (4) The following service information was approved for IBR on 
April 21, 2017 (82 FR 16728, April 6, 2017).
    (i) GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016.
    (ii) [Reserved.]
    (5) For service information identified in this AD, contact 
General Electric Company, 1 Neumann Way, Room 285, Cincinnati, OH 
45215; phone: 513-552-3272; email: [email protected].
    (6) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (7) 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on October 17, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller Standards Branch, Aircraft 
Certification Service.
[FR Doc. 2018-23466 Filed 10-25-18; 8:45 am]
 BILLING CODE 4910-13-P