Airworthiness Directives; CFM International S.A. Turbofan Engines, 66090-66093 [2018-27920]

Download as PDF 66090 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations Issued in Des Moines, Washington, on December 13, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–27881 Filed 12–21–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–1039; Product Identifier 2018–NE–14–AD; Amendment 39– 19531; AD 2018–26–01] RIN 2120–AA64 Airworthiness Directives; CFM International S.A. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 2018–18– 01 for all CFM International S.A. (CFM) Model CFM56–7B turbofan engines. AD 2018–18–01 required initial and repetitive inspections of certain fan blades and, if they fail the inspection, their replacement with parts eligible for installation. This AD requires the same initial and repetitive inspections but revises the compliance time for the initial inspections and revises the installation prohibition based on the updated compliance time. This AD was prompted by further analysis by the manufacturer that indicated a need to reduce the initial fan blade inspection interval based on an ongoing root cause investigation of an April 2018 engine failure. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 10, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 10, 2019. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of May 14, 2018 (83 FR 19176, May 2, 2018). We must receive any comments on this AD by February 11, 2019. 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. amozie on DSK3GDR082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:56 Dec 21, 2018 Jkt 247001 • 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 CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH, 45125; phone: 877–432–3272; fax: 877–432–3329; 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–2018– 1039. 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– 1039; 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 street 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: Christopher McGuire, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781–238–7120; fax: 781–238– 7199; email: chris.mcguire@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued AD 2018–18–01, Amendment 39–19380 (83 FR 49272, October 1, 2018), (‘‘AD 2018–18–01’’), for all CFM model CFM56–7B turbofan engines. AD 2018–18–01 required initial and repetitive ultrasonic inspections (USI) or eddy current inspection (ECI) of certain fan blades and, if they fail the inspection, their replacement with parts eligible for installation. AD 2018–18–01 resulted from analysis by the manufacturer that indicated a need to PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 reduce the repetitive fan blade inspection interval based on ongoing root cause investigation of an April 2018 engine failure. The April 2018 engine failure was the result of a fractured fan blade leading to the engine inlet cowl disintegrating and debris penetrating the fuselage, causing a loss of pressurization and prompting an emergency descent. One passenger fatality occurred as a result. We issued AD 2018–18–01 to reduce the repetitive inspection interval from 3,000 cycles to 1,600 cycles. Actions Since AD 2018–18–01 Was Issued Since we issued AD 2018–18–01, CFM gained a better understanding of the fan blade failures based on the inspections and further analysis of the detected cracks and the April 2018 event. As a result, CFM has published CFM International Service Bulletin (SB) CFM56–7B S/B 72–1033, Revision 3, dated November 6, 2018, to reduce the initial inspection requirement from 20,000 cycles since new (CSN) to 17,000 CSN. We are issuing this AD to address the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 We reviewed CFM International SB CFM56–7B S/B 72–1033, Revision 3, dated November 6, 2018, and Subtask 72–21–01–220–091, of Task 72–21–01– 200–001, from the CFM56–7B Engine Shop Manual (ESM), Revision 57, dated January 15, 2018. CFM International SB CFM56–7B S/B 72–1033, Revision 3, describes procedures for performing a USI of the affected fan blades. Subtask 72–21–01–220–091, of Task 72–21–01– 200–001, from the CFM56–7B ESM, describes procedures for performing an ECI of the affected fan blades. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Other Related Service Information We also reviewed CFM SB CFM56–7B S/B 72–1019, dated March 24, 2017; CFM SB CFM56–7B S/B 72–1019, Revision 1, dated June 13, 2017; CFM SB CFM56–7B S/B 72–1024, dated July 26, 2017; CFM International SB CFM56– 7B S/B 72–1033, Revision 2, dated July 27, 2018; CFM SB CFM56–7B S/B 72– 1033, Revision 1, dated May 9, 2018; CFM SB CFM56–7B S/B 72–1033, dated April 20, 2018; and General Electric Field Support Technology (FST) Procedure 2370, dated December 9, 2016. These SBs and the FST provide information on performing the USI. E:\FR\FM\26DER1.SGM 26DER1 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations 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 initial and repetitive USI or ECI of certain fan blades and, if they fail the inspection, their replacement with parts eligible for installation. Interim Action We consider this AD interim action. An investigation to determine the cause of the failure is ongoing, and we may consider additional rulemaking if final action is identified. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. 66091 The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule. Due to the reduction in the initial inspection interval, some fan blades have reached or exceeded the revised initial inspection threshold and will require inspection within 1,000 cycles after the effective date of this AD. Because of this, the compliance time for the required action is shorter than the time necessary for the public to comment and for the FAA to issue the final rule to ensure the unsafe condition is addressed. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reasons stated above, we find that good cause exists for making this amendment effective in less than 30 days. However, we invite you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2018–1039 and product identifier 2018–NE–14–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. We will consider all comments received by the closing date and may amend this final rule because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this final rule. Comments Invited Costs of Compliance 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. We estimate that this AD affects 3,716 engines installed on 1,858 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED INSPECTION COSTS Action Labor cost Inspect engine fan blade ................................ 2 work-hours × $85 per hour = $170 ............. We estimate the following costs to complete any necessary replacement of a single fan blade that would be Cost per product Parts cost required based on the results of the inspection. We have no way of $0 $170 Cost on U.S. operators $631,720 determining the number of engines that might need fan blades to be replaced. amozie on DSK3GDR082PROD with RULES ON-CONDITION COSTS Action Labor cost Replace fan blade ........................................................ 1 work-hour × $85 per hour = $85 ............................... 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 VerDate Sep<11>2014 16:56 Dec 21, 2018 Jkt 247001 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. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Parts cost $51,400 Cost per product $51,485 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 E:\FR\FM\26DER1.SGM 26DER1 66092 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations (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 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2018–18–01, Amendment 39–19380 (83 FR 49272, October 1, 2018) and adding the following new AD: ■ 2018–26–01 CFM International S.A.: Amendment 39–19531; Docket No. FAA–2018–1039; Product Identifier 2018–NE–14–AD. (a) Effective Date This AD is effective January 10, 2019. amozie on DSK3GDR082PROD with RULES (b) Affected ADs This AD replaces AD 2018–18–01, Amendment 39–19380 (83 FR 49272, October 1, 2018). (c) Applicability This AD applies to CFM International S.A.(CFM) CFM56–7B20, CFM56–7B22, CFM56–7B22/B1, CFM56–7B24, CFM56– 7B24/B1, CFM56–7B26, CFM56–7B26/B2, CFM56–7B27, CFM56–7B27A, CFM56–7B26/ B1, CFM56–7B27/B1, CFM56–7B27/B3, CFM56–7B20/2, CFM56–7B22/2, CFM56– 7B24/2, CFM56–7B26/2, CFM56–7B27/2, CFM56–7B20/3, CFM56–7B22/3, CFM56– 7B22/3B1, CFM56–7B24/3, CFM56–7B24/ 3B1, CFM56–7B26/3, CFM56–7B26/3B1, CFM56–7B26/3B2, CFM56–7B27/3, CFM56– 7B27/3B1, CFM56–7B27/3B3, CFM56– 7B27A/3, CFM56–7B26/3F, CFM56–7B26/ 3B2F, CFM56–7B27/3F, CFM56–7B27/3B1F, CFM56–7B20E, CFM56–7B22E, CFM56– 7B22E/B1, CFM56–7B24E, CFM56–7B24E/ B1, CFM56–7B26E, CFM56–7B26E/B1, CFM56–7B26E/B2, CFM56–7B27AE, CFM56–7B27E, CFM56–7B27E/B1, CFM56– 7B27E/B3, CFM56–7B26E/F, CFM56–7B26E/ B2F, CFM56–7B27E/F, and CFM56–7B27E/ B1F turbofan engine models. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. VerDate Sep<11>2014 16:56 Dec 21, 2018 Jkt 247001 This AD was prompted by further analysis by the manufacturer that indicated a need to reduce the initial fan blade inspection requirement based on its ongoing root cause investigation of an April 2018 engine failure that resulted in one fatality. We are issuing this AD to prevent failure of the fan blade. The unsafe condition, if not addressed, could result in failure of the fan blade, the engine inlet cowl disintegrating and debris penetrating the fuselage, causing a loss of pressurization, and prompting an emergency descent. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions ■ § 39.13 (e) Unsafe Condition (1) Perform an ultrasonic inspection (USI) or eddy current inspection (ECI) of the concave and convex sides of the fan blade dovetail as follows: (i) For a fan blade with less than or equal to 16,000 cycles since new (CSN), inspect prior to accumulating 17,000 CSN. (ii) For a fan blade with more than 16,000 and less than 20,000 CSN, inspect within 1,000 cycles but no later than 20,000 CSN. (iii) For a fan blade with 20,000 or more CSN, inspect before further flight. (iv) Thereafter, repeat this inspection no later than 1,600 cycles since the last inspection, or within 450 cycles after October 16, 2018, the effective date of AD 2018–18– 01, whichever occurs later. (v) Use the Accomplishment Instructions, paragraphs 3.A.(3)(a) through (i), of CFM International Service Bulletin (SB) CFM56– 7B S/B 72–1033, Revision 3, dated November 6, 2018, to perform a USI or use the instructions in subtask 72–21–01–220–091, of task 72–21–01–200–001, from CFM CFM56–7B Engine Shop Manual, Revision 57, dated January 15, 2018, to perform an ECI. (2) If any unserviceable indication, as specified in the applicable service information in paragraph (g)(1)(v) of this AD, is found during the inspections required by paragraph (g) of this AD, replace the fan blade before further flight with a part eligible for installation. (h) Installation Prohibition Do not install any replacement fan blade unless it meets one of the following criteria: (1) The replacement fan blade has fewer than 17,000 CSN, or; (2) The replacement fan blade has been inspected, per paragraph (g)(1) of this AD, within the last 1,600 cycles before installation. (i) Definition For the purpose of this AD, a ‘‘replacement fan blade’’ is a fan blade that is being installed into an engine from which it was not previously removed. Removing and reinstalling a fan blade for the purpose of relubrication is not subject to the Installation Prohibition of this AD. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 (j) Credit for Previous Actions You may take credit for the actions that are required by paragraph (g) of this AD, if you performed those actions before the effective date of this AD using CFM SB CFM56–7B S/ B 72–1019, dated March 24, 2017; CFM SB CFM56–7B S/B 72–1019, Revision 1, dated June 13, 2017; CFM SB CFM56–7B S/B 72– 1024, dated July 26, 2017; CFM SB CFM56– 7B S/B 72–1033 dated April 20, 2018; CFM SB CFM56–7B S/B 72–1033, Revision 1, dated May 9, 2018; or CFM International SB CFM56–7B S/B 72–1033, Revision 2, dated July 27, 2018; or performed an ECI using the instructions in task 72–21–01–200–001, subtask 72–21–01–220–091 of CFM56–7B Engine Shop Manual, earlier than Revision 57, dated January 15, 2018. (k) 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 (l) 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. (3) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(3)(i) and (k)(3)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (4) AMOCs approved previously for AD 2018–10–11 (83 FR 22836, May 17, 2018) and AD 2018–18–01 (83 FR 49272, October 1, 2018) are approved as AMOCs for the corresponding provisions of this AD. (l) Related Information For more information about this AD, contact Christopher McGuire, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7120; fax: 781–238–7199; email: chris.mcguire@faa.gov. (m) 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. E:\FR\FM\26DER1.SGM 26DER1 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations (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 10, 2019. (i) CFM International (CFM) Service Bulletin CFM56–7B S/B 72–1033, Revision 3, dated November 6, 2018. (ii) [Reserved] (4) The following service information was approved for IBR on May 14, 2018 (83 FR 19176, May 2, 2018). (i) Subtask 72–21–01–220–091, of Task 72– 21–01–200–001, from the CFM CFM56–7B Engine Shop Manual, Revision 57, dated January 15, 2018. (ii) [Reserved] (5) For CFM service information identified in this AD, contact CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: 877–432–3272; fax: 877–432–3329; email: aviation.fleetsupport@ge.com. (6) 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. (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 December 18, 2018. Robert J. Ganley, Manager, Engine & Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–27920 Filed 12–21–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0669; Product Identifier 2017–SW–041–AD; Amendment 39–19532; AD 2018–26–02] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2016–25– 19 for Airbus Helicopters (previously Eurocopter France) Model AS350B3 and EC130B4 helicopters. AD 2016–25–19 required inspecting the pilot’s and copilot’s throttle twist for proper operation. This new AD retains the amozie on DSK3GDR082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:56 Dec 21, 2018 Jkt 247001 requirements of AD 2016–25–19 and adds certain model helicopters to the applicability. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective January 30, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 30, 2019. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of February 2, 2017 (81 FR 95854, December 29, 2016). ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.helicopters.airbus.com/website/ en/ref/Technical-Support_73.html. You may the review service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0669. Examining the AD Docket You may examine the AD docket on the internet at http:// www.regulations.gov in Docket No. FAA–2018–0669; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporatedby-reference service information, the economic 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: George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email george.schwab@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2016–25–19, Amendment 39–18745 (81 FR 95854, December 29, 2016) (AD 2016–25–19) PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 66093 and add a new AD. AD 2016–25–19 applied to Airbus Helicopters Model AS350B3 and EC130B4 helicopters with an ARRIEL 2B1 engine with the twochannel Full Authority Digital Engine Control (FADEC) and with new twist grip modification (MOD) 073254 (for the Model AS350B3 helicopter) or MOD 073773 (for the Model EC130B4 helicopter). AD 2016–25–19 required repetitively inspecting the wiring, performing an insulation test, inspecting the pilot and copilot throttle twist grip controls, and testing the pilot and copilot throttle twist grip controls for proper functioning. The actions required in AD 2016–25–19 were intended to prevent unintended touchdown to the ground at a flight-idle power setting during a practice autorotation, damage to the helicopter, and injury to occupants. The NPRM published in the Federal Register on August 8, 2018 (83 FR 39007). The NPRM proposed to retain the requirements of AD 2016–25–19 and expand the applicability by adding Model AS350B3 helicopters with an ARRIEL 2D engine installed and Model EC130T2 helicopters with an ARRIEL 2D engine installed. The NPRM was prompted by AD No. 2017–0059, dated April 6, 2017 (EASA AD 2017–0059), issued by EASA, which is the Technical Agent for the Member States of the European Union, for Airbus Helicopters Model AS 350 B3, EC 130 B4, and EC 130 T2 helicopters. EASA advises that Airbus Helicopters added clarifications to the operational procedure, introduced a modification to apply water-tight protection to the microswitch connectors, and extended the applicability to helicopters with a Turbomeca ARRIEL 2D engine installed. Accordingly, EASA AD 2017–0059 retains the required actions and corrects the applicability of the previous EASA AD. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air E:\FR\FM\26DER1.SGM 26DER1

Agencies

[Federal Register Volume 83, Number 246 (Wednesday, December 26, 2018)]
[Rules and Regulations]
[Pages 66090-66093]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-27920]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1039; Product Identifier 2018-NE-14-AD; Amendment 
39-19531; AD 2018-26-01]
RIN 2120-AA64


Airworthiness Directives; CFM International S.A. Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2018-18-01 for 
all CFM International S.A. (CFM) Model CFM56-7B turbofan engines. AD 
2018-18-01 required initial and repetitive inspections of certain fan 
blades and, if they fail the inspection, their replacement with parts 
eligible for installation. This AD requires the same initial and 
repetitive inspections but revises the compliance time for the initial 
inspections and revises the installation prohibition based on the 
updated compliance time. This AD was prompted by further analysis by 
the manufacturer that indicated a need to reduce the initial fan blade 
inspection interval based on an ongoing root cause investigation of an 
April 2018 engine failure. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective January 10, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 10, 
2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of May 14, 
2018 (83 FR 19176, May 2, 2018).
    We must receive any comments on this AD by February 11, 2019.

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 CFM 
International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 
285, Cincinnati, OH, 45125; phone: 877-432-3272; fax: 877-432-3329; 
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-2018-1039.

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-
1039; 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 street 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: Christopher McGuire, Aerospace 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; 
phone: 781-238-7120; fax: 781-238-7199; email: chris.mcguire@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued AD 2018-18-01, Amendment 39-19380 (83 FR 49272, October 
1, 2018), (``AD 2018-18-01''), for all CFM model CFM56-7B turbofan 
engines. AD 2018-18-01 required initial and repetitive ultrasonic 
inspections (USI) or eddy current inspection (ECI) of certain fan 
blades and, if they fail the inspection, their replacement with parts 
eligible for installation. AD 2018-18-01 resulted from analysis by the 
manufacturer that indicated a need to reduce the repetitive fan blade 
inspection interval based on ongoing root cause investigation of an 
April 2018 engine failure. The April 2018 engine failure was the result 
of a fractured fan blade leading to the engine inlet cowl 
disintegrating and debris penetrating the fuselage, causing a loss of 
pressurization and prompting an emergency descent. One passenger 
fatality occurred as a result. We issued AD 2018-18-01 to reduce the 
repetitive inspection interval from 3,000 cycles to 1,600 cycles.

Actions Since AD 2018-18-01 Was Issued

    Since we issued AD 2018-18-01, CFM gained a better understanding of 
the fan blade failures based on the inspections and further analysis of 
the detected cracks and the April 2018 event. As a result, CFM has 
published CFM International Service Bulletin (SB) CFM56-7B S/B 72-1033, 
Revision 3, dated November 6, 2018, to reduce the initial inspection 
requirement from 20,000 cycles since new (CSN) to 17,000 CSN. We are 
issuing this AD to address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed CFM International SB CFM56-7B S/B 72-1033, Revision 3, 
dated November 6, 2018, and Subtask 72-21-01-220-091, of Task 72-21-01-
200-001, from the CFM56-7B Engine Shop Manual (ESM), Revision 57, dated 
January 15, 2018. CFM International SB CFM56-7B S/B 72-1033, Revision 
3, describes procedures for performing a USI of the affected fan 
blades. Subtask 72-21-01-220-091, of Task 72-21-01-200-001, from the 
CFM56-7B ESM, describes procedures for performing an ECI of the 
affected fan blades. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or by the means identified in the ADDRESSES section.

Other Related Service Information

    We also reviewed CFM SB CFM56-7B S/B 72-1019, dated March 24, 2017; 
CFM SB CFM56-7B S/B 72-1019, Revision 1, dated June 13, 2017; CFM SB 
CFM56-7B S/B 72-1024, dated July 26, 2017; CFM International SB CFM56-
7B S/B 72-1033, Revision 2, dated July 27, 2018; CFM SB CFM56-7B S/B 
72-1033, Revision 1, dated May 9, 2018; CFM SB CFM56-7B S/B 72-1033, 
dated April 20, 2018; and General Electric Field Support Technology 
(FST) Procedure 2370, dated December 9, 2016. These SBs and the FST 
provide information on performing the USI.

[[Page 66091]]

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 initial and repetitive USI or ECI of certain fan 
blades and, if they fail the inspection, their replacement with parts 
eligible for installation.

Interim Action

    We consider this AD interim action. An investigation to determine 
the cause of the failure is ongoing, and we may consider additional 
rulemaking if final action is identified.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule. 
Due to the reduction in the initial inspection interval, some fan 
blades have reached or exceeded the revised initial inspection 
threshold and will require inspection within 1,000 cycles after the 
effective date of this AD. Because of this, the compliance time for the 
required action is shorter than the time necessary for the public to 
comment and for the FAA to issue the final rule to ensure the unsafe 
condition is addressed. Therefore, we find good cause that notice and 
opportunity for prior public comment are impracticable. In addition, 
for the reasons stated above, we find that good cause exists for making 
this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and 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 final 
rule. Send your comments to an address listed under the ADDRESSES 
section. Include the docket number FAA-2018-1039 and product identifier 
2018-NE-14-AD at the beginning of your comments. We specifically invite 
comments on the overall regulatory, economic, environmental, and energy 
aspects of this final rule. We will consider all comments received by 
the closing date and may amend this final rule because of those 
comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

Costs of Compliance

    We estimate that this AD affects 3,716 engines installed on 1,858 
airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                           Estimated Inspection Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect engine fan blade..............  2 work-hours x $85 per                $0            $170        $631,720
                                         hour = $170.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to complete any necessary 
replacement of a single fan blade that would be required based on the 
results of the inspection. We have no way of determining the number of 
engines that might need fan blades to be replaced.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace fan blade.............................  1 work-hour x $85 per hour = $85         $51,400         $51,485
----------------------------------------------------------------------------------------------------------------

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

[[Page 66092]]

    (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) 
2018-18-01, Amendment 39-19380 (83 FR 49272, October 1, 2018) and 
adding the following new AD:

2018-26-01 CFM International S.A.: Amendment 39-19531; Docket No. 
FAA-2018-1039; Product Identifier 2018-NE-14-AD.

(a) Effective Date

    This AD is effective January 10, 2019.

(b) Affected ADs

    This AD replaces AD 2018-18-01, Amendment 39-19380 (83 FR 49272, 
October 1, 2018).

(c) Applicability

    This AD applies to CFM International S.A.(CFM) CFM56-7B20, 
CFM56-7B22, CFM56-7B22/B1, CFM56-7B24, CFM56-7B24/B1, CFM56-7B26, 
CFM56-7B26/B2, CFM56-7B27, CFM56-7B27A, CFM56-7B26/B1, CFM56-7B27/
B1, CFM56-7B27/B3, CFM56-7B20/2, CFM56-7B22/2, CFM56-7B24/2, CFM56-
7B26/2, CFM56-7B27/2, CFM56-7B20/3, CFM56-7B22/3, CFM56-7B22/3B1, 
CFM56-7B24/3, CFM56-7B24/3B1, CFM56-7B26/3, CFM56-7B26/3B1, CFM56-
7B26/3B2, CFM56-7B27/3, CFM56-7B27/3B1, CFM56-7B27/3B3, CFM56-7B27A/
3, CFM56-7B26/3F, CFM56-7B26/3B2F, CFM56-7B27/3F, CFM56-7B27/3B1F, 
CFM56-7B20E, CFM56-7B22E, CFM56-7B22E/B1, CFM56-7B24E, CFM56-7B24E/
B1, CFM56-7B26E, CFM56-7B26E/B1, CFM56-7B26E/B2, CFM56-7B27AE, 
CFM56-7B27E, CFM56-7B27E/B1, CFM56-7B27E/B3, CFM56-7B26E/F, CFM56-
7B26E/B2F, CFM56-7B27E/F, and CFM56-7B27E/B1F turbofan engine 
models.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by further analysis by the manufacturer 
that indicated a need to reduce the initial fan blade inspection 
requirement based on its ongoing root cause investigation of an 
April 2018 engine failure that resulted in one fatality. We are 
issuing this AD to prevent failure of the fan blade. The unsafe 
condition, if not addressed, could result in failure of the fan 
blade, the engine inlet cowl disintegrating and debris penetrating 
the fuselage, causing a loss of pressurization, and prompting an 
emergency descent.

(f) Compliance

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

(g) Required Actions

    (1) Perform an ultrasonic inspection (USI) or eddy current 
inspection (ECI) of the concave and convex sides of the fan blade 
dovetail as follows:
    (i) For a fan blade with less than or equal to 16,000 cycles 
since new (CSN), inspect prior to accumulating 17,000 CSN.
    (ii) For a fan blade with more than 16,000 and less than 20,000 
CSN, inspect within 1,000 cycles but no later than 20,000 CSN.
    (iii) For a fan blade with 20,000 or more CSN, inspect before 
further flight.
    (iv) Thereafter, repeat this inspection no later than 1,600 
cycles since the last inspection, or within 450 cycles after October 
16, 2018, the effective date of AD 2018-18-01, whichever occurs 
later.
    (v) Use the Accomplishment Instructions, paragraphs 3.A.(3)(a) 
through (i), of CFM International Service Bulletin (SB) CFM56-7B S/B 
72-1033, Revision 3, dated November 6, 2018, to perform a USI or use 
the instructions in subtask 72-21-01-220-091, of task 72-21-01-200-
001, from CFM CFM56-7B Engine Shop Manual, Revision 57, dated 
January 15, 2018, to perform an ECI.
    (2) If any unserviceable indication, as specified in the 
applicable service information in paragraph (g)(1)(v) of this AD, is 
found during the inspections required by paragraph (g) of this AD, 
replace the fan blade before further flight with a part eligible for 
installation.

(h) Installation Prohibition

    Do not install any replacement fan blade unless it meets one of 
the following criteria:
    (1) The replacement fan blade has fewer than 17,000 CSN, or;
    (2) The replacement fan blade has been inspected, per paragraph 
(g)(1) of this AD, within the last 1,600 cycles before installation.

(i) Definition

    For the purpose of this AD, a ``replacement fan blade'' is a fan 
blade that is being installed into an engine from which it was not 
previously removed. Removing and reinstalling a fan blade for the 
purpose of relubrication is not subject to the Installation 
Prohibition of this AD.

(j) Credit for Previous Actions

    You may take credit for the actions that are required by 
paragraph (g) of this AD, if you performed those actions before the 
effective date of this AD using CFM SB CFM56-7B S/B 72-1019, dated 
March 24, 2017; CFM SB CFM56-7B S/B 72-1019, Revision 1, dated June 
13, 2017; CFM SB CFM56-7B S/B 72-1024, dated July 26, 2017; CFM SB 
CFM56-7B S/B 72-1033 dated April 20, 2018; CFM SB CFM56-7B S/B 72-
1033, Revision 1, dated May 9, 2018; or CFM International SB CFM56-
7B S/B 72-1033, Revision 2, dated July 27, 2018; or performed an ECI 
using the instructions in task 72-21-01-200-001, subtask 72-21-01-
220-091 of CFM56-7B Engine Shop Manual, earlier than Revision 57, 
dated January 15, 2018.

(k) 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 (l) 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.
    (3) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(k)(3)(i) and (k)(3)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.
    (4) AMOCs approved previously for AD 2018-10-11 (83 FR 22836, 
May 17, 2018) and AD 2018-18-01 (83 FR 49272, October 1, 2018) are 
approved as AMOCs for the corresponding provisions of this AD.

(l) Related Information

    For more information about this AD, contact Christopher McGuire, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: 
chris.mcguire@faa.gov.

(m) 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.

[[Page 66093]]

    (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 10, 2019.
    (i) CFM International (CFM) Service Bulletin CFM56-7B S/B 72-
1033, Revision 3, dated November 6, 2018.
    (ii) [Reserved]
    (4) The following service information was approved for IBR on 
May 14, 2018 (83 FR 19176, May 2, 2018).
    (i) Subtask 72-21-01-220-091, of Task 72-21-01-200-001, from the 
CFM CFM56-7B Engine Shop Manual, Revision 57, dated January 15, 
2018.
    (ii) [Reserved]
    (5) For CFM service information identified in this AD, contact 
CFM International Inc., Aviation Operations Center, 1 Neumann Way, 
M/D Room 285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877-
432-3329; email: aviation.fleetsupport@ge.com.
    (6) 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.
    (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 December 18, 2018.
Robert J. Ganley,
Manager, Engine & Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-27920 Filed 12-21-18; 8:45 am]
 BILLING CODE 4910-13-P