Airworthiness Directives; International Aero Engines (IAE) Turbofan Engines, 55614-55617 [2018-24239]

Download as PDF 55614 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations of this AD, as applicable; or within 30 days after the effective date of this AD; whichever occurs later. (2) If the optional revision specified in paragraph (l)(1) of this AD is accomplished: After the maintenance or inspection program has been revised as provided by paragraph (1)(1) of this AD, no alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (m) of this AD. amozie on DSK3GDR082PROD with RULES (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO 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 (n) of this AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@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) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(4)(i) and (m)(4)(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. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. 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. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on December 12, 2018. (i) Boeing Service Bulletin DC10–28–264, dated May 15, 2015. (ii) Boeing Service Bulletin MD11–28–146, dated May 15, 2015. (iii) Boeing Trijet Special Compliance Item Report MDC–02K1003, Revision R, including Appendices A through D, dated May 9, 2018. (4) The following service information was approved for IBR on April 15, 2016 (81 FR 12806, March 11, 2016). (i) Boeing Alert Service Bulletin DC10– 28A253, dated June 5, 2014. (ii) Boeing Service Bulletin DC10–28–256, dated June 24, 2014. (iii) Boeing Alert Service Bulletin MD11– 28A133, dated June 5, 2014. (iv) Boeing Service Bulletin MD11–28–137, dated June 24, 2014. (v) Boeing Trijet Special Compliance Item Report MDC–02K1003, Revision M, including Appendices A through D, dated July 25, 2014. (5) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone: 562–797–1717; internet: https:// www.myboeingfleet.com. (6) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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 Des Moines, Washington, on October 24, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–23822 Filed 11–6–18; 8:45 am] BILLING CODE 4910–13–P (n) Related Information For more information about this AD, contact Serj Harutunian, Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5254; fax: 562–627–5210; email: serj.harutunian@faa.gov. VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0404; Product Identifier 2018–NE–15–AD; Amendment 39– 19468; AD 2018–21–10] RIN 2120–AA64 Airworthiness Directives; International Aero Engines (IAE) Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all International Aero Engines (IAE) PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1127G–JM, PW1127GA–JM, PW1127G1–JM, PW1124G–JM, PW1124G1–JM, and PW1122G–JM turbofan engines. This AD was prompted by reports of in-flight engine shutdowns and aborted take-offs as the result of certain parts affecting the durability of the rear high-pressure compressor (HPC) rotor hub knife edge seal. This AD requires replacing the diffuser case air seal assembly, the highpressure turbine (HPT) 2nd-stage vane assembly, and the HPT 2nd-stage borescope stator vane assembly with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 12, 2018. ADDRESSES: For service information identified in this final rule, contact International Aero Engines, 400 Main Street, East Hartford, CT, 06118; phone: 800–565–0140; email: help24@ pw.utc.com; internet: http:// fleetcare.pw.utc.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–2018–0404. SUMMARY: 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– 0404; 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 E:\FR\FM\07NOR1.SGM 07NOR1 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations information. The address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kevin M. Clark, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7088; fax: 781–238–7199; email: kevin.m.clark@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all IAE PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1127G–JM, PW1127GA–JM, PW1127G1–JM, PW1124G–JM, PW1124G1–JM, and PW1122G–JM turbofan engines. The NPRM published in the Federal Register on June 11, 2018 (83 FR 26887). The NPRM was prompted by reports of in-flight engine shutdowns and aborted take-offs as the result of certain parts affecting the durability of the rear HPC rotor hub knife edge seal. The NPRM proposed to require replacing the diffuser case air seal assembly, the HPT 2nd-stage vane assembly, and the HPT 2nd-stage borescope stator vane assembly with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products. amozie on DSK3GDR082PROD with RULES Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Change Compliance Time Air Line Pilots Association, International (ALPA) requested that paragraph (g) of this AD be changed to indicate by which cycle, hour, or date the ‘‘engine shop visit’’ and associated actions must be accomplished. ALPA stated that ‘‘at the next engine shop visit’’ is not prescriptive enough to ensure that affected parts are identified and removed from service within a timely manner. We disagree. We determined that removal of the affected parts at the next engine shop visit resolves the unsafe condition within our risk guidelines. Therefore, we did not change this AD. Request To Clarify Applicability ALPA requested that we clarify whether engines repaired per paragraph (g) of this AD would be considered VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 ‘‘affected engines’’ as described in AD 2018–04–01 (83 FR 6791, February 15, 2018), and what operational restrictions, if any, would exist on the engines repaired. We partially agree. We agree that engines repaired per paragraph (g) of this AD are not ‘‘affected engines’’ as described in AD 2018–04–01. We disagree that adding clarification in paragraph (g) of this AD is necessary, because we released a Global Alternative Method of Compliance (AMOC) to paragraph (h) of AD 2018– 04–01 (83 FR 6791, February 15, 2018). The Global AMOC removed the operational restrictions on an affected engine if Pratt & Whitney (PW) Alert Service Bulletin (ASB) PW1000G–C–72– 00–0099–00A–930A–D, Issue No. 002, dated March 15, 2018 procedures were performed and the affected parts removed. Therefore, we did not change the AD. Request To Clarify Affected Engine Serial Numbers (ESNs) European Aviation Safety Agency (EASA) requested that we explain why paragraph (c) of this AD is limited to affected engines with ESNs P770450 to P770614, inclusive. EASA noted that PW ASB PW1000G–C–72–00–0099– 00A–930A–D, Issue No. 002, dated March 15, 2018 identifies a substantially larger population, P770101 to P770614 inclusive, of affected engines. We limited this AD to ESNs P770450 to P770614 because the affected part numbers are not known to be installed in earlier engine models. Therefore, we did not change this AD. Request To Limit Applicability All Nippon Airways requested that we limit the paragraph (c) of this AD to affected engines with diffuser case air seal assembly, part number (P/N) 30G4993–01, the HPT 2nd-stage vane assembly, P/N 30G7572, and HPT 2ndstage borescope stator vane assembly, P/N 30G7672, installed. We agree. We revised the paragraph (c) of this AD to list only those engines with ESNs P770450 through P770614 with diffuser case air seal assembly, P/ N 30G4993–01; HPT 2nd-stage vane assembly, P/N 30G7572; and HPT 2ndstage borescope stator vane assembly, P/N 30G7672, installed. Request To Clarify Method of Compliance Hawaiian Airlines stated engines that have incorporated PW ASB PW1000G– C–72–00–0099–00A–930A–D, Issue No. 002, dated March 15, 2018, or later revisions, should be shown as having complied with this AD. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 55615 We agree. PW ASB PW1000G–C–72– 00–0099–00A–930A–D, Issue No. 002, dated March 15, 2018 can be used as a method to comply with paragraph (g) of this AD, because it requires removing and replacing the affected part numbers. Request To Clarify How To Demonstrate Compliance Hawaiian Airlines stated that complying with this AD would require removal of the diffuser case air seal assembly, P/N 30G4993–01; the HPT 2nd-stage vane assembly, P/N 30G7572; and the HPT 2nd-stage borescope stator vane assembly, P/N 30G7672 at the next engine shop visit. However, none of these P/Ns are individually documented by IAE or PW, either upon delivery or on maintenance, repair, and overhaul (MRO) documentation. Therefore, it would be difficult to demonstrate compliance with paragraph (g) of this AD. We disagree. The operator must verify that their products comply with paragraph (g) of this AD. If overhaul facilities are used to perform maintenance, then documentation of the work completed must be provided to the operator to verify compliance with paragraph (g) of this AD. Therefore, we did not change this AD. Request To Explain Differences in Applicability Between AD and Service Information EASA requested that we explain why this AD applies to more engine models than PW ASB PW1000G–C–72–00– 0099–00A–930A–D, Issue No. 002, dated March 15, 2018. We disagree. This AD applies to all IAE PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1127G–JM, PW1127GA–JM, PW1127G1–JM, PW1124G–JM, PW1124G1–JM, and PW1122G–JM turbofan engines, because they are approved under type certificate, E00087EN. The PW ASB PW1000G–C– 72–00–0099–00A–930A–D, Issue No. 002, dated March 15, 2018 only applies to PW1100G–JM engine models that are currently in service. Therefore, we did not change this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and E:\FR\FM\07NOR1.SGM 07NOR1 55616 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. describes procedures for the disassembly, removal, and replacement of the diffuser case air seal assembly, P/ N 30G4993–01; the HPT 2nd-stage vane assembly, P/N 30G7572; and the HPT 2nd-stage borescope stator vane assembly, P/N 30G7672. Related Service Information We reviewed PW ASB PW1000G–C– 72–00–0099–00A–930A–D, Issue No. 002, dated March 15, 2018. This ASB Interim Action We consider this AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. Costs of Compliance We estimate that this AD affects 16 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Removing and replacing parts ........................ 0 work-hours × $85 per hour = $0 ................. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. amozie on DSK3GDR082PROD with RULES 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 VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 Parts cost $44,000 Cost per product $44,000 Cost on U.S. operators $704,000 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. (c) Applicability This AD applies to International Aero Engines (IAE) PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1127G–JM, PW1127GA– JM, PW1127G1–JM, PW1124G–JM, PW1124G1–JM, and PW1122G–JM turbofan engines with engine serial numbers (ESNs) P770450 through P770614, and with diffuser case air seal assembly part number (P/Ns) 30G4993–01, high-pressure turbine (HPT) 2nd-stage vane assembly, P/N 30G7572, or HPT 2nd-stage borescope stator vane assembly, P/N 30G7672, installed. List of Subjects in 14 CFR Part 39 (e) Unsafe Condition This AD was prompted by reports of inflight engine shutdowns and aborted take-offs that were the result of a failed knife edge seal on affected engines with ESNs P770450 through P770614. We are issuing this AD to prevent failure of the rear high-pressure compressor rotor hub knife edge seal. The unsafe condition, if not addressed, could result in failure of one or more engines, loss of thrust control, and loss of the airplane. 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): ■ 2018–21–10 International Aero Engines: Amendment 39–19468; Docket No. FAA–2018–0404; Product Identifier 2018–NE–15–AD. (a) Effective Date This AD is effective December 12, 2018. (b) Affected ADs None. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions At the next engine shop visit after the effective date of this AD, do the following: (1) Remove from service the diffuser case air seal assembly, P/N 30G4993–01, and replace with a part eligible for installation. (2) Remove from service the HPT 2nd-stage vane assembly, P/N 30G7572, and replace with a part eligible for installation. (3) Remove from service HPT 2nd-stage borescope stator vane assembly, P/N 30G7672, and replace with a part eligible for installation. (h) Definition For the purpose of this AD, an ’’engine shop visit’’ is the induction of an engine into the shop for maintenance involving the E:\FR\FM\07NOR1.SGM 07NOR1 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations separation of pairs of major mating engine flanges (lettered flanges). The separation of engine flanges solely for the purpose of transportation of the engine without subsequent engine maintenance does not constitute an engine shop visit. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. You may email your request to: 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. (j) Related Information For more information about this AD, contact Kevin M. Clark, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7088; fax: 781–238–7199; email: kevin.m.clark@faa.gov. (k) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on October 31, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–24239 Filed 11–6–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0908; Product Identifier 2018–NM–136–AD; Amendment 39–19486; AD 2018–22–13] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350–941 and –1041 airplanes. This AD was prompted by a technical issue detected on the inboard aileron electro-hydrostatic actuators that caused potential erroneous monitoring of those actuators. This AD requires amozie on DSK3GDR082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 revising the airplane flight manual to provide the flightcrew with updated procedures related to inboard aileron fault operations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective November 23, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 23, 2018. We must receive comments on this AD by December 24, 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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continued-airworthiness.a350@ airbus.com; internet http:// www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0908. 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– 0908; 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 regulatory evaluation, any comments received, and other information. The street address for Docket Operations (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 55617 FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2018–0213, dated October 1, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A350–941 and -1041 airplanes. The MCAI states: A technical issue was detected on the inboard aileron electro-hydrostatic actuators, causing potential erroneous monitoring of those actuators. Consequently, in-flight loss of inboard aileron control may occur, which, due to the resulting drag, would lead to increased fuel consumption. This condition, if not corrected, and if combined with one engine inoperative, could result in reduced control or performance of the aeroplane. To address this potential unsafe condition, Airbus issued the AFM [airplane flight manual] TR [temporary revision] and Flight Operations Transmission (FOT) 999.0062/18, informing operators that Airbus provides two different Airbus Temporary Quick Changes (ATQC) to the Electronic Centralized Aircraft Monitoring (ECAM), depending on the installed FWS [flight warning system] standard, either STD S4/2.0 or STD S5/2.2, as applicable, and issued the applicable SB [service bulletin] accordingly, providing modification instructions. For the reasons described above, this [EASA] AD requires amendment of the applicable AFM and installation of ATQC V4, followed by ECAM Temporary Change (ETC) activation, to update the procedures related to inboard aileron fault operations. This AD is considered to be an interim action and further AD action may follow. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0908. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus A350 Temporary Revision (TR) 113, Issue 1.0, dated July 27, 2018, which provides updated procedures related to inboard aileron fault operations. 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. E:\FR\FM\07NOR1.SGM 07NOR1

Agencies

[Federal Register Volume 83, Number 216 (Wednesday, November 7, 2018)]
[Rules and Regulations]
[Pages 55614-55617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24239]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0404; Product Identifier 2018-NE-15-AD; Amendment 
39-19468; AD 2018-21-10]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines (IAE) 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
International Aero Engines (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM, 
PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and 
PW1122G-JM turbofan engines. This AD was prompted by reports of in-
flight engine shutdowns and aborted take-offs as the result of certain 
parts affecting the durability of the rear high-pressure compressor 
(HPC) rotor hub knife edge seal. This AD requires replacing the 
diffuser case air seal assembly, the high-pressure turbine (HPT) 2nd-
stage vane assembly, and the HPT 2nd-stage borescope stator vane 
assembly with parts eligible for installation. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective December 12, 2018.

ADDRESSES: For service information identified in this final rule, 
contact International Aero Engines, 400 Main Street, East Hartford, CT, 
06118; phone: 800-565-0140; email: [email protected]; internet: http://fleetcare.pw.utc.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-2018-0404.

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-
0404; 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

[[Page 55615]]

information. The address for Docket Operations (phone: 800-647-5527) is 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Kevin M. Clark, Aerospace Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
781-238-7088; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all IAE PW1133G-JM, 
PW1133GA-JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-
JM, PW1124G1-JM, and PW1122G-JM turbofan engines. The NPRM published in 
the Federal Register on June 11, 2018 (83 FR 26887). The NPRM was 
prompted by reports of in-flight engine shutdowns and aborted take-offs 
as the result of certain parts affecting the durability of the rear HPC 
rotor hub knife edge seal. The NPRM proposed to require replacing the 
diffuser case air seal assembly, the HPT 2nd-stage vane assembly, and 
the HPT 2nd-stage borescope stator vane assembly with parts eligible 
for installation. We are issuing this AD to address the unsafe 
condition on these products.

Comments

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

Request To Change Compliance Time

    Air Line Pilots Association, International (ALPA) requested that 
paragraph (g) of this AD be changed to indicate by which cycle, hour, 
or date the ``engine shop visit'' and associated actions must be 
accomplished. ALPA stated that ``at the next engine shop visit'' is not 
prescriptive enough to ensure that affected parts are identified and 
removed from service within a timely manner.
    We disagree. We determined that removal of the affected parts at 
the next engine shop visit resolves the unsafe condition within our 
risk guidelines. Therefore, we did not change this AD.

Request To Clarify Applicability

    ALPA requested that we clarify whether engines repaired per 
paragraph (g) of this AD would be considered ``affected engines'' as 
described in AD 2018-04-01 (83 FR 6791, February 15, 2018), and what 
operational restrictions, if any, would exist on the engines repaired.
    We partially agree. We agree that engines repaired per paragraph 
(g) of this AD are not ``affected engines'' as described in AD 2018-04-
01. We disagree that adding clarification in paragraph (g) of this AD 
is necessary, because we released a Global Alternative Method of 
Compliance (AMOC) to paragraph (h) of AD 2018-04-01 (83 FR 6791, 
February 15, 2018). The Global AMOC removed the operational 
restrictions on an affected engine if Pratt & Whitney (PW) Alert 
Service Bulletin (ASB) PW1000G-C-72-00-0099-00A-930A-D, Issue No. 002, 
dated March 15, 2018 procedures were performed and the affected parts 
removed. Therefore, we did not change the AD.

Request To Clarify Affected Engine Serial Numbers (ESNs)

    European Aviation Safety Agency (EASA) requested that we explain 
why paragraph (c) of this AD is limited to affected engines with ESNs 
P770450 to P770614, inclusive. EASA noted that PW ASB PW1000G-C-72-00-
0099-00A-930A-D, Issue No. 002, dated March 15, 2018 identifies a 
substantially larger population, P770101 to P770614 inclusive, of 
affected engines.
    We limited this AD to ESNs P770450 to P770614 because the affected 
part numbers are not known to be installed in earlier engine models. 
Therefore, we did not change this AD.

Request To Limit Applicability

    All Nippon Airways requested that we limit the paragraph (c) of 
this AD to affected engines with diffuser case air seal assembly, part 
number (P/N) 30G4993-01, the HPT 2nd-stage vane assembly, P/N 30G7572, 
and HPT 2nd-stage borescope stator vane assembly, P/N 30G7672, 
installed.
    We agree. We revised the paragraph (c) of this AD to list only 
those engines with ESNs P770450 through P770614 with diffuser case air 
seal assembly, P/N 30G4993-01; HPT 2nd-stage vane assembly, P/N 
30G7572; and HPT 2nd-stage borescope stator vane assembly, P/N 30G7672, 
installed.

Request To Clarify Method of Compliance

    Hawaiian Airlines stated engines that have incorporated PW ASB 
PW1000G-C-72-00-0099-00A-930A-D, Issue No. 002, dated March 15, 2018, 
or later revisions, should be shown as having complied with this AD.
    We agree. PW ASB PW1000G-C-72-00-0099-00A-930A-D, Issue No. 002, 
dated March 15, 2018 can be used as a method to comply with paragraph 
(g) of this AD, because it requires removing and replacing the affected 
part numbers.

Request To Clarify How To Demonstrate Compliance

    Hawaiian Airlines stated that complying with this AD would require 
removal of the diffuser case air seal assembly, P/N 30G4993-01; the HPT 
2nd-stage vane assembly, P/N 30G7572; and the HPT 2nd-stage borescope 
stator vane assembly, P/N 30G7672 at the next engine shop visit. 
However, none of these P/Ns are individually documented by IAE or PW, 
either upon delivery or on maintenance, repair, and overhaul (MRO) 
documentation. Therefore, it would be difficult to demonstrate 
compliance with paragraph (g) of this AD.
    We disagree. The operator must verify that their products comply 
with paragraph (g) of this AD. If overhaul facilities are used to 
perform maintenance, then documentation of the work completed must be 
provided to the operator to verify compliance with paragraph (g) of 
this AD. Therefore, we did not change this AD.

Request To Explain Differences in Applicability Between AD and Service 
Information

    EASA requested that we explain why this AD applies to more engine 
models than PW ASB PW1000G-C-72-00-0099-00A-930A-D, Issue No. 002, 
dated March 15, 2018.
    We disagree. This AD applies to all IAE PW1133G-JM, PW1133GA-JM, 
PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-
JM, and PW1122G-JM turbofan engines, because they are approved under 
type certificate, E00087EN. The PW ASB PW1000G-C-72-00-0099-00A-930A-D, 
Issue No. 002, dated March 15, 2018 only applies to PW1100G-JM engine 
models that are currently in service. Therefore, we did not change this 
AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and

[[Page 55616]]

     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    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

    We reviewed PW ASB PW1000G-C-72-00-0099-00A-930A-D, Issue No. 002, 
dated March 15, 2018. This ASB describes procedures for the 
disassembly, removal, and replacement of the diffuser case air seal 
assembly, P/N 30G4993-01; the HPT 2nd-stage vane assembly, P/N 30G7572; 
and the HPT 2nd-stage borescope stator vane assembly, P/N 30G7672.

Interim Action

    We consider this AD interim action. The manufacturer is currently 
developing a modification that will address the unsafe condition 
identified in this AD. Once this modification is developed, approved, 
and available, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this AD affects 16 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Removing and replacing parts..........  0 work-hours x $85 per           $44,000         $44,000        $704,000
                                         hour = $0.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    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):

2018-21-10 International Aero Engines: Amendment 39-19468; Docket 
No. FAA-2018-0404; Product Identifier 2018-NE-15-AD.

(a) Effective Date

    This AD is effective December 12, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to International Aero Engines (IAE) PW1133G-JM, 
PW1133GA-JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, 
PW1124G-JM, PW1124G1-JM, and PW1122G-JM turbofan engines with engine 
serial numbers (ESNs) P770450 through P770614, and with diffuser 
case air seal assembly part number (P/Ns) 30G4993-01, high-pressure 
turbine (HPT) 2nd-stage vane assembly, P/N 30G7572, or HPT 2nd-stage 
borescope stator vane assembly, P/N 30G7672, installed.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of in-flight engine shutdowns 
and aborted take-offs that were the result of a failed knife edge 
seal on affected engines with ESNs P770450 through P770614. We are 
issuing this AD to prevent failure of the rear high-pressure 
compressor rotor hub knife edge seal. The unsafe condition, if not 
addressed, could result in failure of one or more engines, loss of 
thrust control, and loss of the airplane.

(f) Compliance

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

(g) Required Actions

    At the next engine shop visit after the effective date of this 
AD, do the following:
    (1) Remove from service the diffuser case air seal assembly, P/N 
30G4993-01, and replace with a part eligible for installation.
    (2) Remove from service the HPT 2nd-stage vane assembly, P/N 
30G7572, and replace with a part eligible for installation.
    (3) Remove from service HPT 2nd-stage borescope stator vane 
assembly, P/N 30G7672, and replace with a part eligible for 
installation.

(h) Definition

    For the purpose of this AD, an ''engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the

[[Page 55617]]

separation of pairs of major mating engine flanges (lettered 
flanges). The separation of engine flanges solely for the purpose of 
transportation of the engine without subsequent engine maintenance 
does not constitute an engine shop visit.

(i) Alternative Methods of Compliance (AMOCs)

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

(j) Related Information

    For more information about this AD, contact Kevin M. Clark, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7088; fax: 781-238-7199; email: 
[email protected].

(k) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on October 31, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-24239 Filed 11-6-18; 8:45 am]
 BILLING CODE 4910-13-P