Airworthiness Directives; General Electric Company Turbofan Engines, 43739-43742 [2018-18576]

Download as PDF 43739 Rules and Regulations Federal Register Vol. 83, No. 167 Tuesday, August 28, 2018 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. II. Administrative Requirements The Code of Federal Regulations is sold by the Superintendent of Documents. A. Notice and Comment Requirements Under 5 U.S.C. 553 FEDERAL FINANCIAL INSTITUTIONS EXAMINATION COUNCIL 12 CFR Part 1102 [Docket No. AS18–10] Appraisal Subcommittee; Appraiser Regulation Appraisal Subcommittee of the Federal Financial Institutions Examination Council (ASC). ACTION: Final rule amendments. AGENCY: The ASC is adopting nonsubstantive amendments to its regulations. The amendments correct the street address for the ASC’s office, which will be moved October 1, 2018, from 1401 H Street NW, Suite 760, Washington, DC 20005, to 1325 G Street NW, Suite 500, Washington, DC 20005. DATES: Effective October 1, 2018. FOR FURTHER INFORMATION CONTACT: Alice M. Ritter, General Counsel, at (202) 595–7577 or alice@asc.gov; Appraisal Subcommittee; 1401 H Street NW, Suite 760, Washington, DC 20005. SUPPLEMENTARY INFORMATION: SUMMARY: daltland on DSKBBV9HB2PROD with RULES I. Authority and Section-by-Section Analysis The ASC, since its creation under Title XI of the Financial Institutions Reform, Recovery, and Enforcement Act of 1989, as amended (Title XI), has adopted and amended several regulations that appear at 12 CFR part 1102. These regulations, found in subparts A, B, C, D and E of that part, relate to the ASC’s implementation of The Privacy Act of 1974, the Freedom of Information Act, and various sections of Title XI. On October 1, 2018, the ASC is moving its offices to 1325 G Street NW, Suite 500. Part 1102, as adopted, contains references to the ASC’s previous addresses at 2000 K Street and 2100 Pennsylvania Avenue, as well as the present address at 1401 H Street NW. The ASC is amending part 1102 by VerDate Sep<11>2014 15:59 Aug 27, 2018 Jkt 244001 removing references to the K Street address, the Pennsylvania Avenue address and the H Street address, and replacing it with its new G Street address. The ASC, under 12 U.S.C. 553, is required, among other things, to publish in the Federal Register for public notice and comment a general notice of proposed rulemaking, unless, in accordance with paragraph (b)(3)(B), the agency finds ‘‘for good cause . . . that notice and public procedure thereon are impracticable, unnecessary, or contrary to the public interest.’’ The ASC finds that notice and procedure are unnecessary in connection with these rule amendments because they are nonsubstantive and essentially are nomenclature changes, as that term is defined in the Federal Register Document Drafting Handbook, page 2– 33, Revision 7 (May 15, 2018). c. Remove the words ‘‘2000 K Street NW, Suite 310, Washington, DC’’ wherever they appear and add in their place the words, ‘‘1325 G Street NW, Suite 500, Washington DC 20005’’; and ■ d. Remove the words ‘‘1401 H Street NW, Suite 760, Washington, DC 20005’’ wherever they appear and add in their place the words, ‘‘1325 G Street NW, Suite 500, Washington, DC 20005’’. ■ By the Appraisal Subcommittee. Dated: August 21, 2018. James R. Park, Executive Director. [FR Doc. 2018–18566 Filed 8–27–18; 8:45 am] BILLING CODE 6700–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0792; Product Identifier 2017–NE–28–AD; Amendment 39– 19336; AD 2018–15–04] List of Subjects in 12 CFR Part 1102 RIN 2120–AA64 Administrative practice and procedure, Appraisers, Banks, Banking, Freedom of information, Mortgages, Reporting and recordkeeping requirements. Airworthiness Directives; General Electric Company Turbofan Engines Text of the Rule For the reasons set forth in the preamble, title 12, chapter XI of the Code of Federal Regulations is amended as follows: PART 1102—APPRAISER REGULATION 1. The authority citation for part 1102 continues to read as follows: ■ Authority: 12 U.S.C. 3348(a), 3332, 3335, 3338 (a)(4)(B), 3348(c), 5 U.S.C. 552a, 553(e); Executive Order 12600, 52 FR 23781 (3 CFR, 1987 Comp., p. 235). 2. In part 1102: a. Remove the words ‘‘2100 Pennsylvania Avenue NW, Suite 200, Washington, DC 20037’’ wherever they appear and add in their place the words, ‘‘1325 G Street NW, Suite 500, Washington, DC 20005’’; ■ b. Remove the words ‘‘2000 K Street NW, Suite 310, Washington, DC 20006’’ wherever they appear and add in their place the words, ‘‘1325 G Street NW, Suite 500, Washington, DC 20005’’; ■ ■ PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF6– 80A, CF6–80A1, CF6–80A2, CF6–80A3, CF6–80C2A1, CF6–80C2A2, CF6– 80C2A3, CF6–80C2A5, CF6–80C2A5F, CF6–80C2A8, CF6–80C2B1, CF6– 80C2B1F, CF6–80C2B2, CF6–80C2B2F, CF6–80C2B4, CF6–80C2B4F, CF6– 80C2B5F, CF6–80C2B6, CF6–80C2B6F, CF6–80C2B6FA, CF6–80C2B7F, CF6– 80C2D1F, CF6–80C2L1F, and CF6– 80C2K1F turbofan engines. This AD was prompted by an uncontained failure of a high-pressure turbine (HPT) stage 2 disk that resulted in a fire. This AD requires ultrasonic inspection (UI) of HPT stage 1 and 2 disks. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 2, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 2, 2018. SUMMARY: E:\FR\FM\28AUR1.SGM 28AUR1 43740 Federal Register / Vol. 83, No. 167 / Tuesday, August 28, 2018 / Rules and Regulations For service information identified in this final rule, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH, 45215; phone: 513–552–3272; email: aviation.fleetsupport@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–2017– 0792. ADDRESSES: daltland on DSKBBV9HB2PROD with RULES 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–2017– 0792; 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 Docket Operations, 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: 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. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain GE CF6– 80A, CF6–80A1, CF6–80A2, CF6–80A3, CF6–80C2A1, CF6–80C2A2, CF6– 80C2A3, CF6–80C2A5, CF6–80C2A5F, CF6–80C2A8, CF6–80C2B1, CF6– 80C2B1F, CF6–80C2B2, CF6–80C2B2F, CF6–80C2B4, CF6–80C2B4F, CF6– 80C2B5F, CF6–80C2B6, CF6–80C2B6F, CF6–80C2B6FA, CF6–80C2B7F, CF6– 80C2D1F, CF6–80C2L1F, and CF6– 80C2K1F turbofan engines with HPT disks with part numbers and serial numbers (S/Ns) listed in Table 1 and 2 of Appendix A in GE Service Bulletin (SB) CF6–80C2 SB 72–1562 R03, dated January 10, 2018 and Table 1 of Appendix A in GE SB CF6–80A SB 72– 0869 R01, dated October 19, 2017. The SNPRM published in the Federal VerDate Sep<11>2014 15:59 Aug 27, 2018 Jkt 244001 Register on March 30, 2018 (83 FR 13703). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on September 7, 2017 (82 FR 42261). The NPRM proposed to require UI of HPT stage 1 and 2 disks. The NPRM was prompted by an uncontained failure of an HPT stage 2 disk that resulted in a fire. The SNPRM proposed to require the same UI of HPT stage 1 and 2 disks, remove certain engine models, and to add a new part number to the applicability of this AD. The SNPRM also proposed to revise references to the service information in this AD because, since the publication of the NPRM, GE published the list of affected HPT S/Ns in two separate SBs applicable to the CF6–80A and CF6– 80C2 engines. 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 final rule. The following presents the comments received on the SNPRM and the FAA’s response to each comment. Request To Change the Applicability All Nippon Airways (ANA) and Japan Airlines (JAL) requested that we change the applicability, paragraph (c), to include S/Ns that are listed in revisions of GE CF6–80C2 SB 72–1562 and GE CF6–80A SB 72–0869 that have not yet been published. ANA and JAL reasoned that the SB revisions will include an updated list of affected S/Ns. We disagree. While future SB revisions may include additional affected S/Ns, we do not require compliance based on service information that has not been published. The applicability of this AD is based on the most recently published service information. Any further change in applicability would require a notice and comment rulemaking for those affected S/Ns. We did not change this AD. Request To Improve the UI Criteria JAL requested that we improve the UI criteria to avoid false-positive indications resulting in rejection of disks. JAL reasoned that GE may publish a GE CF6–80C2 SB 72–1562 revision in which GE will modify the UI criteria. We disagree. While a future SB revision may include updated UI criteria, we do not require compliance based on service information that has not yet been published. We based the UI PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 criteria on the most recently published service information. We will review any Alternative Methods of Compliance (AMOC) requests submitted if different UI criteria, not specified in this AD, are desired. We did not change this AD. Request To Change the Definition of ‘‘Piece-Part Exposure’’ ANA requested that we change the definition of ‘‘piece-part exposure’’ to the separation of the HPT stage 1 or stage 2 disk from the thermal shield within the HPT rotor module. We disagree. The current definition is sufficient to describe the piece-part exposure. We did not change this AD. Support for the AD Boeing Company, FedEx, and United Airlines expressed support for the SNPRM as written. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 We reviewed GE CF6–80C2 SB 72– 1562 R03, dated January 10, 2018. The SB describes procedures for UI of CF6– 80C2 turbofan engine HPT stage 1 and 2 disks. We also reviewed GE CF6–80A SB 72–0869 R01, dated October 19, 2017. The SB describes procedures for UI of CF6–80A turbofan engine HPT stage 2 disks. 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 640 HPT disks on engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\28AUR1.SGM 28AUR1 Federal Register / Vol. 83, No. 167 / Tuesday, August 28, 2018 / Rules and Regulations 43741 ESTIMATED COSTS Action Labor cost UI of HPT disk ................................................ 10 work-hours × $85 per hour = $850 ........... daltland on DSKBBV9HB2PROD with RULES 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 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 VerDate Sep<11>2014 15:59 Aug 27, 2018 Jkt 244001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2018–15–04 General Electric Company: Amendment 39–19336; Docket No. FAA–2017–0792; Product Identifier 2017–NE–28–AD. (a) Effective Date This AD is effective October 2, 2018. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) CF6–80A, CF6–80A1, CF6– 80A2, CF6–80A3, CF6–80C2A1, CF6– 80C2A2, CF6–80C2A3, CF6–80C2A5, CF6– 80C2A5F, CF6–80C2A8, CF6–80C2B1, CF6– 80C2B1F, CF6–80C2B2, CF6–80C2B2F, CF6– 80C2B4, CF6–80C2B4F, CF6–80C2B5F, CF6– 80C2B6, CF6–80C2B6F, CF6–80C2B6FA, CF6–80C2B7F, CF6–80C2D1F, CF6– 80C2L1F, and CF6–80C2K1F turbofan engines with high-pressure turbine (HPT) disks with serial numbers listed in Table 1 and 2 of Appendix A in GE CF6–80C2 Service Bulletin (SB) 72–1562 R03, dated January 10, 2018; and Table 1 of Appendix A in GE CF6–80A SB 72–0869 R01, dated October 19, 2017. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine/Turboprop Engine— Turbine Section. (e) Unsafe Condition This AD was prompted by an uncontained failure of an HPT stage 2 disk. We are issuing this AD to prevent failure of the HPT stage 1 disk (CF6–80C2) and the HPT stage 2 disk PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 $850 Cost on U.S. operators $544,000 (CF6–80C2 and CF6–80A). The unsafe condition, if not addressed, could result in an uncontained HPT disk 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 After the effective date of this AD, perform an ultrasonic inspection (UI) for cracks in HPT stage 1 and stage 2 disks on the CF6– 80C2 turbofan engine and in HPT stage 2 disks on the CF6–80A turbofan engine at each piece-part level exposure in accordance with the Accomplishment Instructions, paragraph 3.A.(2), in GE CF6–80C2 SB 72– 1562 R03, dated January 10, 2018, or the Accomplishment Instructions, paragraph 3.A.(2) in GE CF6–80A SB 72–0869 R01, dated October 19, 2017, as applicable to the engine model. (h) Non-Required Actions The reporting requirements specified in the Accomplishment Instructions, paragraphs 3.A.(2)(c) and 3.A.(2)(f), of GE CF6–80C2 SB 72–1562 R03, dated January 10, 2018, are not required by this AD. (i) Definition For the purpose of this AD, ‘‘piece-part exposure’’ of the HPT stage 1 or stage 2 disk is separation of that HPT disk from its mating rotor parts within the HPT rotor module (thermal shield and HPT stage 1 and stage 2 disk respectively). (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office send it to the attention of the person identified in paragraph (k) 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. (k) 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. E:\FR\FM\28AUR1.SGM 28AUR1 43742 Federal Register / Vol. 83, No. 167 / Tuesday, August 28, 2018 / Rules and Regulations (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) General Electric Company (GE) CF6– 80A Service Bulletin (SB) 72–0869 R01, dated October 19, 2017. (ii) GE CF6–80C2 SB 72–1562 R03, dated January 10, 2018. (3) For GE service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH, 45215; phone: 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. (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. [Docket No. FAA–2018–0723; Product Identifier 2018–NE–17–AD; Amendment 39– 19350; AD 2018–16–10] airplane caused by one propeller going to a negative thrust position during the landing approach. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 12, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 12, 2018. We must receive comments on this AD by October 12, 2018. 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 http://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 final rule, contact GE Aviation Czech s.r.o., Beranovy´ch 65, 199 02 Praha 9—Letnˇany, Czech Republic; phone: +420 222 538 111; fax: +420 222 538 222. 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–2018–0723. RIN 2120–AA64 Examining the AD Docket Issued in Burlington, Massachusetts, on August 21, 2018. Karen M. Grant, Acting Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–18576 Filed 8–27–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain GE Aviation Czech H80–200 turboprop engines. This AD requires replacing the beta switch and adjusting the engine push-pull control to prevent the propeller governor control from going to a negative thrust position. This AD was prompted by an accident involving an Aircraft Industries (AI) L 410 UVP–E20 daltland on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:59 Aug 27, 2018 Jkt 244001 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0723; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647– 5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, ECO PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7134; fax: 781–238–7199; email: wego.wang@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2018– 0075, dated April 5, 2018 (referred to after this as ‘‘the MCAI’’), to address an unsafe condition for the specified products. The MCAI states: A fatal accident of an L 410 UVP–E20 aeroplane has been reported. Preliminary investigation determined that there was an annunciation of Beta mode on right hand engine, that the propeller went inadvertently behind the fine pitch position and reached a negative thrust position, and that the pitch lock system did not intervene. This event occurred on approach at a speed and altitude which did not allow the crew to recover this control system malfunction. This condition, if not corrected, could lead to reduced control or loss of control of the aeroplane. To address this unsafe condition, GE Aviation Czech issued the SB, providing modification instructions. For the reason described above, this [EASA] AD requires modification of the engine. Addressing the same unsafe condition at aeroplane level, EASA also issued AD 2018–0057, requiring modification of affected AI L 410 UVP–E20 and L 410 UVP–E20 CARGO aeroplanes, if equipped with GE Aviation H80–200 engines and Avia Propeller AV 725 propellers. You may obtain further information by examining the MCAI in the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0723. Related Service Information Under 1 CFR Part 51 We reviewed GE Aviation Czech Service Bulletin (SB) SB–H80–76–00– 00–0036, Revision No. 02, dated March 29, 2018. The SB describes procedures for inspecting and adjusting engine push-pull control, part number (P/N) M601–76.3, and replacing beta switch, P/N P–S–2, with beta switch, P/N P–S– 2A. 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 This product has been approved by EASA, and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of E:\FR\FM\28AUR1.SGM 28AUR1

Agencies

[Federal Register Volume 83, Number 167 (Tuesday, August 28, 2018)]
[Rules and Regulations]
[Pages 43739-43742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-18576]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0792; Product Identifier 2017-NE-28-AD; Amendment 
39-19336; AD 2018-15-04]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
General Electric Company (GE) CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, 
CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-
80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, 
CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-
80C2B7F, CF6-80C2D1F, CF6-80C2L1F, and CF6-80C2K1F turbofan engines. 
This AD was prompted by an uncontained failure of a high-pressure 
turbine (HPT) stage 2 disk that resulted in a fire. This AD requires 
ultrasonic inspection (UI) of HPT stage 1 and 2 disks. We are issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective October 2, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 2, 
2018.

[[Page 43740]]


ADDRESSES: For service information identified in this final rule, 
contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
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-2017-0792.

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-2017-
0792; 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 Docket Operations, 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: Matthew Smith, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781-
238-7735; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to certain GE 
CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-
80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, 
CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-
80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2D1F, CF6-
80C2L1F, and CF6-80C2K1F turbofan engines with HPT disks with part 
numbers and serial numbers (S/Ns) listed in Table 1 and 2 of Appendix A 
in GE Service Bulletin (SB) CF6-80C2 SB 72-1562 R03, dated January 10, 
2018 and Table 1 of Appendix A in GE SB CF6-80A SB 72-0869 R01, dated 
October 19, 2017. The SNPRM published in the Federal Register on March 
30, 2018 (83 FR 13703). We preceded the SNPRM with a notice of proposed 
rulemaking (NPRM) that published in the Federal Register on September 
7, 2017 (82 FR 42261). The NPRM proposed to require UI of HPT stage 1 
and 2 disks. The NPRM was prompted by an uncontained failure of an HPT 
stage 2 disk that resulted in a fire. The SNPRM proposed to require the 
same UI of HPT stage 1 and 2 disks, remove certain engine models, and 
to add a new part number to the applicability of this AD. The SNPRM 
also proposed to revise references to the service information in this 
AD because, since the publication of the NPRM, GE published the list of 
affected HPT S/Ns in two separate SBs applicable to the CF6-80A and 
CF6-80C2 engines. 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 final rule. The following presents the comments received on the 
SNPRM and the FAA's response to each comment.

Request To Change the Applicability

    All Nippon Airways (ANA) and Japan Airlines (JAL) requested that we 
change the applicability, paragraph (c), to include S/Ns that are 
listed in revisions of GE CF6-80C2 SB 72-1562 and GE CF6-80A SB 72-0869 
that have not yet been published. ANA and JAL reasoned that the SB 
revisions will include an updated list of affected S/Ns.
    We disagree. While future SB revisions may include additional 
affected S/Ns, we do not require compliance based on service 
information that has not been published. The applicability of this AD 
is based on the most recently published service information. Any 
further change in applicability would require a notice and comment 
rulemaking for those affected S/Ns. We did not change this AD.

Request To Improve the UI Criteria

    JAL requested that we improve the UI criteria to avoid false-
positive indications resulting in rejection of disks. JAL reasoned that 
GE may publish a GE CF6-80C2 SB 72-1562 revision in which GE will 
modify the UI criteria.
    We disagree. While a future SB revision may include updated UI 
criteria, we do not require compliance based on service information 
that has not yet been published. We based the UI criteria on the most 
recently published service information. We will review any Alternative 
Methods of Compliance (AMOC) requests submitted if different UI 
criteria, not specified in this AD, are desired. We did not change this 
AD.

Request To Change the Definition of ``Piece-Part Exposure''

    ANA requested that we change the definition of ``piece-part 
exposure'' to the separation of the HPT stage 1 or stage 2 disk from 
the thermal shield within the HPT rotor module.
    We disagree. The current definition is sufficient to describe the 
piece-part exposure. We did not change this AD.

Support for the AD

    Boeing Company, FedEx, and United Airlines expressed support for 
the SNPRM as written.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    We reviewed GE CF6-80C2 SB 72-1562 R03, dated January 10, 2018. The 
SB describes procedures for UI of CF6-80C2 turbofan engine HPT stage 1 
and 2 disks. We also reviewed GE CF6-80A SB 72-0869 R01, dated October 
19, 2017. The SB describes procedures for UI of CF6-80A turbofan engine 
HPT stage 2 disks. 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 640 HPT disks on engines installed 
on airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 43741]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
UI of HPT disk........................  10 work-hours x $85 per               $0            $850        $544,000
                                         hour = $850.
----------------------------------------------------------------------------------------------------------------

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

    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 adding the following new airworthiness 
directive (AD):

2018-15-04 General Electric Company: Amendment 39-19336; Docket No. 
FAA-2017-0792; Product Identifier 2017-NE-28-AD.

(a) Effective Date

    This AD is effective October 2, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF6-80A, CF6-
80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-
80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-
80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-
80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2D1F, CF6-
80C2L1F, and CF6-80C2K1F turbofan engines with high-pressure turbine 
(HPT) disks with serial numbers listed in Table 1 and 2 of Appendix 
A in GE CF6-80C2 Service Bulletin (SB) 72-1562 R03, dated January 
10, 2018; and Table 1 of Appendix A in GE CF6-80A SB 72-0869 R01, 
dated October 19, 2017.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine/
Turboprop Engine--Turbine Section.

(e) Unsafe Condition

    This AD was prompted by an uncontained failure of an HPT stage 2 
disk. We are issuing this AD to prevent failure of the HPT stage 1 
disk (CF6-80C2) and the HPT stage 2 disk (CF6-80C2 and CF6-80A). The 
unsafe condition, if not addressed, could result in an uncontained 
HPT disk 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

    After the effective date of this AD, perform an ultrasonic 
inspection (UI) for cracks in HPT stage 1 and stage 2 disks on the 
CF6-80C2 turbofan engine and in HPT stage 2 disks on the CF6-80A 
turbofan engine at each piece-part level exposure in accordance with 
the Accomplishment Instructions, paragraph 3.A.(2), in GE CF6-80C2 
SB 72-1562 R03, dated January 10, 2018, or the Accomplishment 
Instructions, paragraph 3.A.(2) in GE CF6-80A SB 72-0869 R01, dated 
October 19, 2017, as applicable to the engine model.

(h) Non-Required Actions

    The reporting requirements specified in the Accomplishment 
Instructions, paragraphs 3.A.(2)(c) and 3.A.(2)(f), of GE CF6-80C2 
SB 72-1562 R03, dated January 10, 2018, are not required by this AD.

(i) Definition

    For the purpose of this AD, ``piece-part exposure'' of the HPT 
stage 1 or stage 2 disk is separation of that HPT disk from its 
mating rotor parts within the HPT rotor module (thermal shield and 
HPT stage 1 and stage 2 disk respectively).

(j) Alternative Methods of Compliance (AMOCs)

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

(k) 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: [email protected].

[[Page 43742]]

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) General Electric Company (GE) CF6-80A Service Bulletin (SB) 
72-0869 R01, dated October 19, 2017.
    (ii) GE CF6-80C2 SB 72-1562 R03, dated January 10, 2018.
    (3) For GE service information identified in this AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH, 45215; phone: 513-552-3272; email: 
[email protected].
    (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.
    (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/ibr-locations.html.

    Issued in Burlington, Massachusetts, on August 21, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller Standards Branch, Aircraft 
Certification Service.
[FR Doc. 2018-18576 Filed 8-27-18; 8:45 am]
 BILLING CODE 4910-13-P