Airworthiness Directives; International Aero Engines Turbofan Engines, 55619-55626 [2018-24250]

Download as PDF Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations 2018–22–13 Airbus SAS: Amendment 39– 19486; Docket No. FAA–2018–0908; Product Identifier 2018–NM–136–AD. (a) Effective Date This AD becomes effective November 23, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A350–941 and -1041 airplanes, certificated in any category, except those on which the modifications specified in paragraph (c)(1) or (c)(2) of this AD, as applicable, have been embodied in production. (1) Airbus modifications 113759 and 113758. (2) Airbus modifications 113760 and 113758. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Reason This AD was prompted by a technical issue detected on the inboard aileron electrohydrostatic actuators that caused potential erroneous monitoring of those actuators. We are issuing this AD to address possible inflight loss of inboard aileron control, consequent increased fuel consumption due to the resulting drag, and reduced control or performance of the airplane if one engine is also inoperative. amozie on DSK3GDR082PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Revision of the Airplane Flight Manual (AFM) Within 30 days after the effective date of this AD, revise the Abnormal Procedures section of the AFM to include the information in Airbus A350 Temporary Revision (TR) 113, Issue 1.0, dated July 27, 2018, which introduces updated procedures related to inboard aileron fault operations. This may be done by inserting a copy of TR 113, Issue 1.0, dated July 27, 2018, into the AFM. When TR 113, Issue 1.0, dated July 27, 2018, has been included in general revisions of the AFM, the general revisions may be inserted into the AFM, provided the relevant information in the general revisions is identical to that in TR 113, Issue 1.0, dated July 27, 2018, and the TR may be removed. Operate the airplane according to the procedures in TR 113, Issue 1.0, dated July 27, 2018. In case any discrepancy is identified between procedures displayed on the electronic centralized aircraft monitoring (ECAM) and procedures stated in the applicable AFM, the AFM procedures prevail. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 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 International Section, send it to the attention of the person identified in paragraph (i)(2) of this AD. Information may be emailed to 9-ANM-116-AMOCREQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified 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 procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2018–0213, dated October 1, 2018, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2018–0908. (2) For more information about this AD, 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. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus A350 Temporary Revision (TR) 113, Issue 1.0, dated July 27, 2018. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 55619 telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continuedairworthiness.a350@airbus.com; internet http://www.airbus.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on October 22, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–23991 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–2018–0431; Product Identifier 2018–NE–16–AD; Amendment 39– 19475; AD 2018–22–02] RIN 2120–AA64 Airworthiness Directives; International Aero Engines 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 with a certain high-pressure compressor (HPC) front hub installed. This AD was prompted by corrosion found on the HPC front hub. This AD requires replacing the HPC front hub with a part 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 (IAE), 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 SUMMARY: E:\FR\FM\07NOR1.SGM 07NOR1 55620 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations 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–2018–0431. 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– 0431; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, 20590. FOR FURTHER INFORMATION CONTACT: 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 IAE PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1127G–JM, PW1127GA–JM, PW1127G1–JM, PW1124G–JM, PW1124G1–JM, and PW1122G–JM turbofan engines with a certain HPC front hub installed. The NPRM published in the Federal Register on June 28, 2018 (83 FR 30370). The NPRM was prompted by a report that corrosion was found on HPC front hub, part number (P/N) 30G2401. The HPC front hub exhibited deposits that could not be removed using standard procedures and worsened over time. After further investigation, pitting corrosion was found below the painted surface. This condition, if not addressed, could result in uncontained HPC front hub release, damage to the engine, and damage to the airplane. The NPRM proposed to require replacing the HPC front hub with a part 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. We have considered the comment received on the NPRM and the FAA’s response to each comment. Request Clarification on CSN Limit All Nippon Airways requested that we clarify which cycles since new (CSN) limit for this AD is correct. ANA stated the PW Service Bulletin PW1000G–C–72–00–0106–00A–930A– D, dated June 15, 2018 specifies a limit of 4,400 cycles since new (CSN), while paragraph (g) of this AD specifies a limit of 4,440 CSN. We disagree. The AD limit of 4,440 CSN is correct. We found that 4,440 CSN provides an acceptable level of safety, and reducing the CSN limit in this AD to match the SB is not required. Therefore, we did not change this AD. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information We reviewed Section PW1000G–C– 05–10–00–02A–288A–D of the PW1100G–JM Series Airworthiness Limitations Manual, P/N 5316993, dated September 30, 2015. Section PW1000G– C–05–10–00–02A–288A–D provides guidance for an approved FAA method of mixed model cycles since new calculation. 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 Replace HPC front hub ................................... 0 work-hours × $85 per hour = $85 ............... amozie on DSK3GDR082PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 Parts cost 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. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 $11,600 Cost per product $11,600 Cost on U.S. operators $185,600 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\07NOR1.SGM 07NOR1 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 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 14 CFR part 39 as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ AD 2018–22–02 International Aero Engines: Amendment 39–19475; Docket No. FAA–2018–0431; Product Identifier 2018–NE–16–AD. amozie on DSK3GDR082PROD with RULES 16:15 Nov 06, 2018 Jkt 247001 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 a high-pressure compressor (HPC) front hub, part number (P/N) 30G2401, installed. (e) Unsafe Condition 1. The authority citation for part 39 continues to read as follows: VerDate Sep<11>2014 (c) Applicability Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. ■ (a) Effective Date This AD is effective December 12, 2018. None. (d) Subject PART 39—AIRWORTHINESS DIRECTIVES § 39.13 (b) Affected ADs This AD was prompted by corrosion found on the HPC front hub, P/N 30G2401, installed. We are issuing this AD to prevent cracking and failure of the HPC front hub. The unsafe condition, if not addressed, could result in uncontained HPC front hub release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Remove from service the HPC front hub, P/ N 30G2401, within 120 days after the effective date of this AD, or as follows, PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 55621 whichever occurs later, and replace with a part eligible for installation: (1) For PW1122G–JM, PW1124G1–JM, PW1124G–JM, PW1127G1–JM, PW1127GA– JM, and PW1127G–JM engines, remove the HPC front hub before exceeding 6,180 cycles since new (CSN) or within five years since the ship date listed in Table 1 to paragraph (g) of this AD, whichever occurs first. (2) For PW1130G–JM, PW1133GA–JM, and PW1133G–JM engines, remove the HPC front hub before exceeding 4,440 CSN or within four years since the ship date listed in Table 1 to paragraph (g) of this AD, whichever occurs first. (3) For engines operating as a mix of models listed in paragraphs (g)(1) and (2) of this AD, remove the HPC front hub using a CSN calculated by an approved FAA method or within four years since the ship date listed in Table 1 to paragraph (g) of this AD, whichever occurs first. You may find guidance for an approved FAA method of mixed model CSN calculation in Section PW1000G–C–05–10–00–02A–288A–D of the PW1100G–JM Series Airworthiness Limitations Manual, P/N 5316993, dated September 30, 2015. (4) For any HPC front hub, P/N 30G2401, whose serial number is not listed in Table 1 to paragraph (g) of this AD, use October 21, 2015, as the ship date. BILLING CODE 4910–13–P E:\FR\FM\07NOR1.SGM 07NOR1 55622 Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations Steel Front Hub Serial Number LENCAJ3513 LENCAJ4524 LENCAJ2782 LENCAJ2794 LENCAJ4527 LENCAJ3500 LENCAJ4508 LENCAJ3505 LENCAJ4518 LENCAJ3507 LENCAJ2789 LENCAJ4516 LENCAJ3509 LENCAJ3511 LENCAJ4538 LENCAJ4535 LENCAJ2788 LENCAJ4512 LENCAJ3502 LENCAJ3503 LENCAJ4540 LENCAJ3510 LENCAJ4539 LENCAJ4525 LENCAJ4531 LENCAJ4510 LENCAJ4522 LENCAJ3506 LENCAJ4532 LENCAJ3506 LENCAJ4534 LENCAJ4548 LENCAJ4552 LENCAJ4521 LENCAJ4529 LENCAJ4520 LENCAJ4544 LENCAJ4511 LENCAJ4549 VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00022 Ship Date 10/23/2015 11/6/2015 11125/2015 11/9/2015 11117/2015 11116/2015 11123/2015 6/20/2016 12/2/2015 12/31/2015 12/22/2015 12112/2015 12/31/2015 12/28/2015 1/6/2016 1/8/2016 1/17/2016 1117/2016 1/31/2016 2/7/2016 1/31/2016 2/17/2016 2/14/2016 2/25/2016 2/20/2016 3/14/2016 2/27/2016 2/27/2016 3/11/2016 3/17/2016 3/3112016 6/13/2016 5/6/2016 4/30/2016 4/30/2016 4/28/2016 4/30/2016 8/25/2016 8/26/2016 Fmt 4700 Sfmt 4725 Originally Installed in Engine Serial Number P770121 P770125 P770126 P770127 P770128 P770129 P770130 P770131 P770132 P770133 P770134 P770135 P770136 P770137 P770138 P770139 P770140 P770141 P770142 P770143 P770144 P770145 P770146 P770147 P770148 P770149 P770150 P770151 P770153 P770154 P770155 P770160 P770161 P770163 P770164 P770165 P770166 P770167 P770168 E:\FR\FM\07NOR1.SGM 07NOR1 ER07NO18.001</GPH> amozie on DSK3GDR082PROD with RULES Table 1 to Paragraph (g) - Steel Front Hub Ship Date LENCAJ4553 LENCAJ4551 LENCAJ4517 LENCAJ4543 LENCAJ4513 LENCAJ4550 LENCAJ4530 LENCAJ4533 LENCAJ4515 LENCAJ4563 LENCAJ4545 LENCAJ4542 LENCAJ4546 LENCAJ4566 LENCAJ4558 LENCAJ4507 LENCAK4516 LENCAJ3508 LENCAJ4572 LENCAJ4573 LENCAJ4555 LENCAJ4565 LENCAJ4559 LENCAJ4570 LENCAJ4560 LENCAJ4571 LENCAJ4562 LENCAJ4526 LENCAJ4561 LENCAJ4504 LENCAJ4579 LENCAJ4519 LENCAK4517 LENCAJ4595 LENCAK4523 LENCAK4505 LENCAJ4541 LENCAJ4592 LENCAJ4569 LENCAK4512 LENCAK4518 LENCAK4541 LENCAK4535 VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00023 5/19/2016 5/19/2016 5/21/2016 5/19/2016 5/31/2016 5/20/2016 6/8/2016 5/26/2016 6/8/2016 6/26/2016 6/10/2016 6/10/2016 6/22/2016 6/22/2016 6/23/2016 8/31/2016 8/29/2016 7/8/2016 6/30/2016 6/28/2016 6/29/2016 6/30/2016 7/5/2016 7/16/2016 7/23/2016 7/23/2016 7/25/2016 8/12/2016 8/9/2016 7/29/2016 8/7/2016 8/3/2016 8/9/2016 8/17/2016 8/30/2016 8/15/2016 8/3112016 8/22/2016 9/30/2016 8/29/2016 10/7/2016 8/3112016 9/17/2016 Fmt 4700 Sfmt 4725 55623 P770169 P770170 P770171 P770172 P770173 P770174 P770175 P770176 P770177 P770178 P770179 P770180 P770181 P770182 P770183 P770184 P770185 P770186 P770187 P770188 P770189 P770190 P770191 P770192 P770193 P770194 P770195 P770196 P770197 P770198 P770199 P770200 P770201 P770202 P770203 P770204 P770205 P770206 P770207 P770208 P770210 P770211 P770212 E:\FR\FM\07NOR1.SGM 07NOR1 ER07NO18.002</GPH> amozie on DSK3GDR082PROD with RULES Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations LENCAJ4584 LENCAK4538 LENCAK4533 LENCAJ4594 LENCAJ4509 LENCAK4526 LENCAK4532 LENCAJ4602 LENCAK4513 LENCAK5147 LENCAK4536 LENCAK4522 LENCAJ4578 LENCAJ4596 LENCAJ4575 LENCAJ4577 LENCAJ4597 LENCAJ4588 LENCAK4552 LENCAJ4537 LENCAJ4586 LENCAJ4528 LENCAJ4554 LENCAK4553 LENCAJ4598 LENCAK4550 LENCAJ4603 LENCAJ4585 LENCAK4537 LENCAK4520 LENCAK4528 LENCAK5171 LENCAK4549 LENCAJ4557 LENCAK4515 LENCAJ4601 LENCAK4511 LENCAJ4581 LENCAK5182 LENCAK5153 LENCAJ4576 LENCAK4539 LENCAJ4591 VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00024 9/20/2016 9/3/2016 11/30/2016 9/23/2016 10/25/2016 9/16/2016 9/19/2016 9/22/2016 9/27/2016 10119/2016 10119/2016 9/30/2016 12/29/2016 9/30/2016 10/4/2017 12/5/2016 10112/2016 10/19/2016 10114/2016 10/29/2016 10/21/2016 11118/2016 12/29/2016 11/112016 11118/2016 12/5/2016 12/5/2016 12/5/2016 12/2/2016 1118/2016 12/2/2016 11130/2016 12/5/2016 12/5/2016 12/7/2016 1/8/2017 12/7/2016 2/21/2017 11130/2016 11/30/2016 12112/2016 2/26/2017 8/23/2017 Fmt 4700 Sfmt 4725 P770213 P770214 P770215 P770216 P770217 P770218 P770219 P770220 P770221 P770222 P770223 P770224 P770225 P770226 P770227 P770228 P770229 P770230 P770231 P770232 P770233 P770234 P770235 P770236 P770237 P770238 P770239 P770240 P770241 P770242 P770243 P770244 P770245 P770246 P770247 P770248 P770249 P770250 P770251 P770252 P770253 P770254 P770255 E:\FR\FM\07NOR1.SGM 07NOR1 ER07NO18.003</GPH> amozie on DSK3GDR082PROD with RULES 55624 LENCAK5166 LENCAK5193 LENCAK5149 LENCAK5157 LENCAK5191 LENCAK5176 LENCAK4545 LENCAK5192 LENCAK4548 LENCAK5154 LENCAK5163 LENCAK5184 LENCAK4507 LENCAK5165 LENCAK5173 LENCAJ4589 LENCAK5179 LENCAK4543 LENCAK4510 LENCAK5156 LENCAK5169 LENCAK4524 LENCAK5187 LENCAK5175 LENCAK4546 LENCAK5185 LENCAK5162 LENCAK5150 LENCAK5144 LENCAJ2787 LENCAK4554 LENCAK5186 LENCAK5172 LENCAK5170 LENCAK5155 LENCAK5164 LENCAK5168 LENCAK4514 LENCAK5189 LENCAK7184 LENCAK5146 LENCAK5151 LENCAK5152 VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00025 12/15/2016 12117/2016 12/21/2016 3/28/2017 12/20/2016 12/20/2016 12/21/2016 12/22/2016 12/23/2016 12/27/2016 12/28/2016 12/23/2016 12/31/2016 2/2/2017 12/29/2016 12/29/2016 12/31/2016 1/10/2017 3/3112017 1/17/2017 1116/2017 1/19/2017 1/24/2017 1124/2017 1/25/2017 1124/2017 2/8/2017 8/25/2017 3/31/2017 113112017 1/25/2017 113112017 1/31/2017 113112017 2/6/2017 2/7/2017 2/13/2017 2/14/2017 6/22/2017 2/16/2017 2/28/2017 2/27/2017 8/14/2017 Fmt 4700 Sfmt 4725 55625 P770256 P770258 P770259 P770260 P770261 P770262 P770263 P770264 P770265 P770266 P770267 P770268 P770269 P770270 P770271 P770272 P770273 P770275 P770276 P770277 P770278 P770279 P770280 P770281 P770282 P770283 P770284 P770285 P770286 P770287 P770288 P770289 P770290 P770291 P770292 P770293 P770294 P770295 P770296 P770297 P770298 P770299 P770300 E:\FR\FM\07NOR1.SGM 07NOR1 ER07NO18.004</GPH> amozie on DSK3GDR082PROD with RULES Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations BILLING CODE 4910–13–C (h) 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 (i) 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. amozie on DSK3GDR082PROD with RULES 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. (j) Material Incorporated by Reference None. 16:15 Nov 06, 2018 [Docket No. SSA–2018–0041] The Bipartisan Budget Act of 2018 (BBA 2018) revised the MAGI ranges again for years beginning with 2019. We consider a beneficiary’s MAGI and tax filing status to determine: The percentage of the unsubsidized Medicare Part B premium that the beneficiary must pay; and the percentage of the cost of basic Medicare prescription drug coverage the beneficiary must pay. This final rule makes our regulations consistent with the MAGI ranges specified by MACRA and BBA 2018. RIN 0960–AI37 DATES: Income-Related Monthly Adjustment Amounts for Medicare Part B and Prescription Drug Coverage Premiums FOR FURTHER INFORMATION CONTACT: [FR Doc. 2018–24250 Filed 11–6–18; 8:45 am] BILLING CODE 4910–13–P SOCIAL SECURITY ADMINISTRATION 20 CFR Part 418 Social Security Administration. Final rule. AGENCY: (i) Related Information VerDate Sep<11>2014 Issued in Burlington, MA, on November 01, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. Jkt 247001 ACTION: The Medicare Access and CHIP Reauthorization Act of 2015 (MACRA) changed the modified adjusted gross income (MAGI) ranges associated with Medicare Part B and Medicare prescription drug coverage premiums for years beginning in 2018. SUMMARY: PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 This rule is effective November 7, 2018. Donald Murphy, Office of Income Security Programs, Social Security Administration, 6401 Security Boulevard, Baltimore, MD 21235–6401, (410) 965–9090. For information on eligibility or filing for benefits, call our national toll-free number, 1–800–772– 1213, or TTY 1–800–325–0778, or visit our internet site, Social Security Online, at http://www.socialsecurity.gov. SUPPLEMENTARY INFORMATION: E:\FR\FM\07NOR1.SGM 07NOR1 ER07NO18.005</GPH> 55626

Agencies

[Federal Register Volume 83, Number 216 (Wednesday, November 7, 2018)]
[Rules and Regulations]
[Pages 55619-55626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24250]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0431; Product Identifier 2018-NE-16-AD; Amendment 
39-19475; AD 2018-22-02]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines 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 with a certain high-pressure compressor 
(HPC) front hub installed. This AD was prompted by corrosion found on 
the HPC front hub. This AD requires replacing the HPC front hub with a 
part 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 (IAE), 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

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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-2018-0431.

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-
0431; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC, 20590.

FOR FURTHER INFORMATION CONTACT: 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 IAE PW1133G-JM, PW1133GA-
JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, 
PW1124G1-JM, and PW1122G-JM turbofan engines with a certain HPC front 
hub installed. The NPRM published in the Federal Register on June 28, 
2018 (83 FR 30370). The NPRM was prompted by a report that corrosion 
was found on HPC front hub, part number (P/N) 30G2401. The HPC front 
hub exhibited deposits that could not be removed using standard 
procedures and worsened over time. After further investigation, pitting 
corrosion was found below the painted surface. This condition, if not 
addressed, could result in uncontained HPC front hub release, damage to 
the engine, and damage to the airplane. The NPRM proposed to require 
replacing the HPC front hub with a part 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. We have considered the comment received on the NPRM 
and the FAA's response to each comment.

Request Clarification on CSN Limit

    All Nippon Airways requested that we clarify which cycles since new 
(CSN) limit for this AD is correct. ANA stated the PW Service Bulletin 
PW1000G-C-72-00-0106-00A-930A-D, dated June 15, 2018 specifies a limit 
of 4,400 cycles since new (CSN), while paragraph (g) of this AD 
specifies a limit of 4,440 CSN.
    We disagree. The AD limit of 4,440 CSN is correct. We found that 
4,440 CSN provides an acceptable level of safety, and reducing the CSN 
limit in this AD to match the SB is not required. Therefore, we did not 
change this AD.

Conclusion

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

Related Service Information

    We reviewed Section PW1000G-C-05-10-00-02A-288A-D of the PW1100G-JM 
Series Airworthiness Limitations Manual, P/N 5316993, dated September 
30, 2015. Section PW1000G-C-05-10-00-02A-288A-D provides guidance for 
an approved FAA method of mixed model cycles since new calculation.

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
----------------------------------------------------------------------------------------------------------------
Replace HPC front hub.................  0 work-hours x $85 per           $11,600         $11,600        $185,600
                                         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 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

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    (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):

AD 2018-22-02 International Aero Engines: Amendment 39-19475; Docket 
No. FAA-2018-0431; Product Identifier 2018-NE-16-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 a 
high-pressure compressor (HPC) front hub, part number (P/N) 30G2401, 
installed.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by corrosion found on the HPC front hub, P/
N 30G2401, installed. We are issuing this AD to prevent cracking and 
failure of the HPC front hub. The unsafe condition, if not 
addressed, could result in uncontained HPC front hub release, damage 
to the engine, and damage to the airplane.

(f) Compliance

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

(g) Required Actions

    Remove from service the HPC front hub, P/N 30G2401, within 120 
days after the effective date of this AD, or as follows, whichever 
occurs later, and replace with a part eligible for installation:
    (1) For PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G1-JM, 
PW1127GA-JM, and PW1127G-JM engines, remove the HPC front hub before 
exceeding 6,180 cycles since new (CSN) or within five years since 
the ship date listed in Table 1 to paragraph (g) of this AD, 
whichever occurs first.
    (2) For PW1130G-JM, PW1133GA-JM, and PW1133G-JM engines, remove 
the HPC front hub before exceeding 4,440 CSN or within four years 
since the ship date listed in Table 1 to paragraph (g) of this AD, 
whichever occurs first.
    (3) For engines operating as a mix of models listed in 
paragraphs (g)(1) and (2) of this AD, remove the HPC front hub using 
a CSN calculated by an approved FAA method or within four years 
since the ship date listed in Table 1 to paragraph (g) of this AD, 
whichever occurs first. You may find guidance for an approved FAA 
method of mixed model CSN calculation in Section PW1000G-C-05-10-00-
02A-288A-D of the PW1100G-JM Series Airworthiness Limitations 
Manual, P/N 5316993, dated September 30, 2015.
    (4) For any HPC front hub, P/N 30G2401, whose serial number is 
not listed in Table 1 to paragraph (g) of this AD, use October 21, 
2015, as the ship date.
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(h) 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 (i) 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.

(i) 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].

(j) Material Incorporated by Reference

    None.

    Issued in Burlington, MA, on November 01, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-24250 Filed 11-6-18; 8:45 am]
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