Airworthiness Directives; International Aero Engines Turbofan Engines, 27511-27513 [2019-12360]

Download as PDF Federal Register / Vol. 84, No. 114 / Thursday, June 13, 2019 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0393; Product Identifier 2019–NE–14–AD; Amendment 39– 19654; AD 2019–11–08] RIN 2120–AA64 Airworthiness Directives; International Aero Engines Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines, LLC (IAE) PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1129G–JM, PW1127G–JM, PW1127GA–JM, PW1127G1–JM, PW1124G–JM, PW1124G1–JM, and PW1122G–JM model turbofan engines. This AD requires the removal of the main gearbox (MGB) assembly and electronic engine control (EEC) software and the installation of a part and software version eligible for installation. This AD was prompted by multiple reports of inflight engine shutdowns (IFSDs) as the result of high-cycle fatigue causing fracture of certain parts of the MGB assembly. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 28, 2019. The FAA must receive comments on this AD by July 29, 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 https://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 International Aero Engines, LLC, 400 Main Street, East Hartford, CT 06118; phone: 800– 565–0140; email: help24@pw.utc.com; khammond on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:11 Jun 12, 2019 Jkt 247001 internet: https://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 https://www.regulations.gov by searching for and locating Docket No. FAA–2019– 0393. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0393; 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 the Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. 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 The FAA learned of 13 IFSD events on certain IAE PW1100G–JM model turbofan engines beginning in October, 2018. After further analysis, IAE determined that the integrated drive generator (IDG) oil pump drive gearshaft assembly in the MGB assembly fractured during engine operation as a result of high-cycle fatigue. In response, IAE subsequently redesigned the IDG oil pump drive gearshaft assembly in the MGB assembly with an axially thicker gear web, a radially thicker gear rim, and an improved tooth tip relief to improve MGB assembly durability and reliability. IAE also redesigned the EEC software to restrict engine operation to certain parameters. This condition, if not addressed, could result in failure of one or more engines, loss of thrust control, and loss of the airplane. The FAA is issuing this AD to address the unsafe condition on these products. Related Service Information The FAA reviewed PW Service Bulletin (SB) PW1000G–C–72–00–0129– 00A–930A–D, Original Issue, dated April 18, 2019, and PW SB PW1000G– C–73–00–0037–00A–930A–D, Original Issue, dated May 28, 2019. PW SB PW1000G–C–72–00–0129–00A–930A– D, Original Issue, dated April 18, 2019, PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 27511 describes procedures for replacing the IDG oil pump drive gearshaft assembly in the MGB assembly. PW SB PW1000G–C–73–00–0037–00A–930A– D, Original Issue, dated May 28, 2019, describes procedures for replacing the EEC software to incorporate FCS 5.0 software. FAA’s Determination The FAA is issuing this AD because it 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 the removal of the MGB assembly and EEC software and the installation parts and software versions eligible for installation. Interim Action These actions are interim actions, and the FAA may do additional rulemaking in the future for removal and replacement of the MGB assembly on the engines that do not operate on 180minute or 120-minute extended operations (ETOPS) flights. 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. Multiple IAE PW1100G–JM model turbofan engines experienced MGB assembly failures recently, which resulted in IFSDs. The MGB assemblies must be removed for ETOPS operators within 90 or 120 days after the effective date of this AD, depending on the length of the operator’s ETOPS flights, to ensure the MGB assemblies are replaced before fractures develop that could result in the failure of both MGB assemblies and a dual IFSD event. Therefore, the FAA finds good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reason stated above, the FAA finds 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 was not preceded by notice and an opportunity for public comment. However, the FAA invites you to send any written data, views, or arguments about this final rule. Send your E:\FR\FM\13JNR1.SGM 13JNR1 27512 Federal Register / Vol. 84, No. 114 / Thursday, June 13, 2019 / Rules and Regulations comments to an address listed under the ADDRESSES section. Include the docket number FAA–2019–0393 and Product Identifier 2019–NE–14–AD at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. The FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact received about this final rule. prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without The FAA estimates that this AD affects 72 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: Costs of Compliance khammond on DSKBBV9HB2PROD with RULES ESTIMATED COSTS Action Labor cost Replace the MGB assembly ........................... Replace the EEC software ............................. 13 work-hours × $85 per hour = $1,105 ........ 3 work-hours × $85 per hour = $255 ............. 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. The FAA is 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. 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, and (2) Will not affect intrastate aviation in Alaska. 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 VerDate Sep<11>2014 16:11 Jun 12, 2019 Jkt 247001 Parts cost List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–11–08 International Aero Engines: Amendment 39–19654; Docket No. FAA–2019–0393; Product Identifier 2019–NE–14–AD. (a) Effective Date This AD is effective June 28, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all International Aero Engines, LLC (IAE) PW1133G–JM, PW1133GA–JM, PW1130G–JM, PW1129G– PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 $75,000 0 Cost per product $76,105 255 Cost on U.S. operators $5,479,560 18,360 JM, PW1127G–JM, PW1127GA–JM, PW1127G1–JM, PW1124G–JM, PW1124G1– JM, and PW1122G–JM model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7260, Turbine Engine Accessory Drive. (e) Unsafe Condition This AD was prompted by multiple reports of in-flight engine shutdowns as the result of high-cycle fatigue causing fracture of certain parts of the main gearbox (MGB) assembly. The FAA is issuing this AD to prevent failure of the MGB assembly. 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 (1) Remove the MGB assembly, part number (P/N) 5322505, and install a part eligible for installation as follows: (i) For engines that operate on 180-minute extended operations (ETOPS) flights, within 90 days from the effective date of this AD; (ii) For engines that operate on 120-minute ETOPS flights, within 120 days from the effective date of this AD. (2) For engines with MGB assembly P/N 5322505, within 120 days from the effective date of this AD, remove electronic engine control (EEC) software earlier than FCS 5.0 from the engine and load EEC software that is eligible for installation. (h) Installation Prohibition (1) After the effective date of this AD, do not install integrated drive generator (IDG) oil pump drive gearshaft assembly, P/N 5322630–01, into an MGB assembly. (2) After the effective date of this AD, do not load EEC software earlier than FCS 5.0 on any engine identified in paragraph (c) of this AD with an MGB assembly, P/N 5322505. E:\FR\FM\13JNR1.SGM 13JNR1 Federal Register / Vol. 84, No. 114 / Thursday, June 13, 2019 / Rules and Regulations (i) Definitions (1) For the purpose of this AD, a ‘‘part eligible for installation’’ is an MGB assembly with an IDG oil pump drive gearshaft assembly other than P/N 5322630–01. (2) For the purpose of this AD, ‘‘EEC software that is eligible for installation’’ is EEC software FCS 5.0 and later. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k) of this AD. You may email your request to: ANE-AD-AMOC@ faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (k) Related Information For more information about this AD, contact 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. (l) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on June 6, 2019. Robert J. Ganley, Manager, Engine & Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2019–12360 Filed 6–12–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 1 [TD 9864] RIN 1545–BO89 Contributions in Exchange for State or Local Tax Credits Internal Revenue Service (IRS), Treasury. ACTION: Final regulations. AGENCY: This document contains a final regulation under section 170 of the Internal Revenue Code (Code). The final regulation provides rules governing the availability of charitable contribution deductions under section 170 when a taxpayer receives or expects to receive a corresponding state or local tax credit. This document also provides a final khammond on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:11 Jun 12, 2019 Jkt 247001 regulation under section 642(c) to apply similar rules to payments made by a trust or decedent’s estate. DATES: Effective date: These regulations are effective August 12, 2019. Applicability dates: For dates of applicability, see § 1.170A–1(h)(3)(viii) and § 1.642(c)–3(g)(2). FOR FURTHER INFORMATION CONTACT: Mon L. Lam or Richard C. Gano IV at (202) 317–4059 (not a toll-free number). SUPPLEMENTARY INFORMATION: Background Section 170(a)(1) generally allows an itemized deduction for any ‘‘charitable contribution’’ paid within the taxable year. Section 170(c) defines ‘‘charitable contribution’’ as a ‘‘contribution or gift to or for the use of’’ any entity described in that section. Under section 170(c)(1), such an entity includes a State, a possession of the United States, or any political subdivision of the foregoing, or the District of Columbia. Entities described in section 170(c)(2) include certain corporations, trusts, or community chests, funds, or foundations, organized and operated exclusively for religious, charitable, scientific, literary, or educational purposes, or to foster national or international amateur sports competition, or for the prevention of cruelty to children or animals. To be deductible as a charitable contribution under section 170, a transfer to an entity described in section 170(c) must be a contribution or gift. A contribution or gift for this purpose is a voluntary transfer of money or property without the receipt of adequate consideration, made with charitable intent. In Rev. Rul. 67–246, 1967–2 C.B. 104, the Internal Revenue Service (IRS) addressed the taxpayer’s burden of proof for establishing charitable intent when the taxpayer receives a privilege or benefit in conjunction with its contribution. In this revenue ruling, the IRS set out a two-part test for determining whether the taxpayer is entitled to a charitable contribution deduction under these circumstances. First, the taxpayer has the burden of proving that its payment to the charity exceeds the market value of the privileges or other benefits received. Second, the taxpayer must show that it paid the excess with the intention of making a gift. In United States v. American Bar Endowment, 477 U.S. 105, 116–18 (1986), the Supreme Court elaborated on the test set out in Rev. Rul. 67–246. The Court interpreted the phrase ‘‘charitable contribution’’ in section 170 as it relates PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 27513 to the donor’s receipt of consideration, and stated that the ‘‘sine qua non of a charitable contribution is a transfer of money or property without adequate consideration.’’ Id. at 118. The Court concluded that ‘‘[a] payment of money generally cannot constitute a charitable contribution if the contributor expects a substantial benefit in return,’’ (id. at 116), (hereinafter referred to as the ‘‘quid pro quo principle’’). The Court recognized that some payments may have a ‘‘dual character’’—part charitable contribution and part return benefit. Id. at 117. The Court reasoned that in dual character cases ‘‘it would not serve the purposes of section 170 to deny a deduction altogether’’; therefore, a charitable deduction is allowed, but only to the extent the amount donated or the fair market value of the property transferred by the taxpayer exceeds the fair market value of the benefit received in return, and only if the excess amount was transferred with the intent of making a gift. Id. See also Hernandez v. Commissioner, 490 U.S. 680, 690 (1989) (stating that Congress intended to differentiate between unrequited payments and payments made in return for goods or services). Because this inquiry focuses on the donor’s expectation of a benefit, it does not matter whether the donor expects the benefit from the recipient of the payment or transfer, or from a third party. See, for example, Singer Co. v. United States, 449 F.2d 413, 422–23 (Ct. Cl. 1971); cited with approval in American Bar Endowment, 477 U.S. at 116–17. In Hernandez, 490 U.S. at 690–91, the Supreme Court reaffirmed the quid pro quo standard articulated in American Bar Endowment. Specifically, the Court held that payments to a charity that entitled the taxpayers to receive an identifiable benefit in return for their money were part of a ‘‘quintessential quid pro quo exchange,’’ and thus, were not contributions or gifts within the meaning of section 170. Id. at 691. In making this determination, the Court noted the importance of examining the ‘‘external features of a transaction,’’ thereby ‘‘obviating the need for the IRS to conduct imprecise inquiries into the motivations of individual taxpayers.’’ Id. at 690–91. Thus, both American Bar Endowment and Hernandez indicate that objective considerations guide the determination of whether the taxpayer purposely contributed money or property in excess of the value of any benefit received in return. In addition, these cases continue to recognize the requirement that the taxpayer have charitable intent. See American Bar E:\FR\FM\13JNR1.SGM 13JNR1

Agencies

[Federal Register Volume 84, Number 114 (Thursday, June 13, 2019)]
[Rules and Regulations]
[Pages 27511-27513]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-12360]



[[Page 27511]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0393; Product Identifier 2019-NE-14-AD; Amendment 
39-19654; AD 2019-11-08]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
International Aero Engines, LLC (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-
JM, PW1129G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, 
PW1124G1-JM, and PW1122G-JM model turbofan engines. This AD requires 
the removal of the main gearbox (MGB) assembly and electronic engine 
control (EEC) software and the installation of a part and software 
version eligible for installation. This AD was prompted by multiple 
reports of in-flight engine shutdowns (IFSDs) as the result of high-
cycle fatigue causing fracture of certain parts of the MGB assembly. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective June 28, 2019.
    The FAA must receive comments on this AD by July 29, 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 https://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 
International Aero Engines, LLC, 400 Main Street, East Hartford, CT 
06118; phone: 800-565-0140; email: [email protected]; internet: https://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 https://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0393.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0393; 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 the Docket Operations is 
listed above. Comments will be available in the AD docket shortly after 
receipt.

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

    The FAA learned of 13 IFSD events on certain IAE PW1100G-JM model 
turbofan engines beginning in October, 2018. After further analysis, 
IAE determined that the integrated drive generator (IDG) oil pump drive 
gearshaft assembly in the MGB assembly fractured during engine 
operation as a result of high-cycle fatigue. In response, IAE 
subsequently redesigned the IDG oil pump drive gearshaft assembly in 
the MGB assembly with an axially thicker gear web, a radially thicker 
gear rim, and an improved tooth tip relief to improve MGB assembly 
durability and reliability. IAE also redesigned the EEC software to 
restrict engine operation to certain parameters. This condition, if not 
addressed, could result in failure of one or more engines, loss of 
thrust control, and loss of the airplane. The FAA is issuing this AD to 
address the unsafe condition on these products.

Related Service Information

    The FAA reviewed PW Service Bulletin (SB) PW1000G-C-72-00-0129-00A-
930A-D, Original Issue, dated April 18, 2019, and PW SB PW1000G-C-73-
00-0037-00A-930A-D, Original Issue, dated May 28, 2019. PW SB PW1000G-
C-72-00-0129-00A-930A-D, Original Issue, dated April 18, 2019, 
describes procedures for replacing the IDG oil pump drive gearshaft 
assembly in the MGB assembly. PW SB PW1000G-C-73-00-0037-00A-930A-D, 
Original Issue, dated May 28, 2019, describes procedures for replacing 
the EEC software to incorporate FCS 5.0 software.

FAA's Determination

    The FAA is issuing this AD because it 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 the removal of the MGB assembly and EEC software 
and the installation parts and software versions eligible for 
installation.

Interim Action

    These actions are interim actions, and the FAA may do additional 
rulemaking in the future for removal and replacement of the MGB 
assembly on the engines that do not operate on 180-minute or 120-minute 
extended operations (ETOPS) flights.

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. 
Multiple IAE PW1100G-JM model turbofan engines experienced MGB assembly 
failures recently, which resulted in IFSDs. The MGB assemblies must be 
removed for ETOPS operators within 90 or 120 days after the effective 
date of this AD, depending on the length of the operator's ETOPS 
flights, to ensure the MGB assemblies are replaced before fractures 
develop that could result in the failure of both MGB assemblies and a 
dual IFSD event. Therefore, the FAA finds good cause that notice and 
opportunity for prior public comment are impracticable. In addition, 
for the reason stated above, the FAA finds 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 was not preceded by notice and an opportunity for public 
comment. However, the FAA invites you to send any written data, views, 
or arguments about this final rule. Send your

[[Page 27512]]

comments to an address listed under the ADDRESSES section. Include the 
docket number FAA-2019-0393 and Product Identifier 2019-NE-14-AD at the 
beginning of your comments. The FAA specifically invites comments on 
the overall regulatory, economic, environmental, and energy aspects of 
this final rule. The FAA will consider all comments received by the 
closing date and may amend this final rule because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this final rule.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 72 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace the MGB assembly..............  13 work-hours x $85 per          $75,000         $76,105      $5,479,560
                                         hour = $1,105.
Replace the EEC software..............  3 work-hours x $85 per                 0             255          18,360
                                         hour = $255.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is 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, and
    (2) Will not affect intrastate aviation in Alaska.

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):

2019-11-08 International Aero Engines: Amendment 39-19654; Docket 
No. FAA-2019-0393; Product Identifier 2019-NE-14-AD.

(a) Effective Date

    This AD is effective June 28, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all International Aero Engines, LLC (IAE) 
PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1129G-JM, PW1127G-JM, 
PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and PW1122G-JM 
model turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7260, Turbine Engine 
Accessory Drive.

(e) Unsafe Condition

    This AD was prompted by multiple reports of in-flight engine 
shutdowns as the result of high-cycle fatigue causing fracture of 
certain parts of the main gearbox (MGB) assembly. The FAA is issuing 
this AD to prevent failure of the MGB assembly. 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

    (1) Remove the MGB assembly, part number (P/N) 5322505, and 
install a part eligible for installation as follows:
    (i) For engines that operate on 180-minute extended operations 
(ETOPS) flights, within 90 days from the effective date of this AD;
    (ii) For engines that operate on 120-minute ETOPS flights, 
within 120 days from the effective date of this AD.
    (2) For engines with MGB assembly P/N 5322505, within 120 days 
from the effective date of this AD, remove electronic engine control 
(EEC) software earlier than FCS 5.0 from the engine and load EEC 
software that is eligible for installation.

(h) Installation Prohibition

    (1) After the effective date of this AD, do not install 
integrated drive generator (IDG) oil pump drive gearshaft assembly, 
P/N 5322630-01, into an MGB assembly.
    (2) After the effective date of this AD, do not load EEC 
software earlier than FCS 5.0 on any engine identified in paragraph 
(c) of this AD with an MGB assembly, P/N 5322505.

[[Page 27513]]

(i) Definitions

    (1) For the purpose of this AD, a ``part eligible for 
installation'' is an MGB assembly with an IDG oil pump drive 
gearshaft assembly other than P/N 5322630-01.
    (2) For the purpose of this AD, ``EEC software that is eligible 
for installation'' is EEC software FCS 5.0 and later.

(j) Alternative Methods of Compliance (AMOCs)

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

(k) Related Information

    For more information about this AD, contact 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].

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on June 6, 2019.
Robert J. Ganley,
Manager, Engine & Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-12360 Filed 6-12-19; 8:45 am]
 BILLING CODE 4910-13-P
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