Airworthiness Directives; Engine Alliance Turbofan Engines, 55816-55818 [2018-24386]

Download as PDF 55816 Federal Register / Vol. 83, No. 217 / Thursday, November 8, 2018 / Rules and Regulations BILLING CODE 4910–13–C (h) Inspection Within 3 months after the effective date of this AD, accomplish a detailed inspection to detect discrepancies and structural damage at the wing rib foot locations specified in, and in accordance with Airbus Alert Operators Transmission A57P011–18, dated October 8, 2018. (1) If any discrepancy is detected, do all applicable related investigative and corrective actions before further flight, in accordance with Airbus Alert Operators Transmission A57P011–18, dated October 8, 2018. (2) If any structural damage is detected, before further flight obtain corrective actions 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) and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA-authorized signature. (i) Relief From MEL Restrictions After accomplishment of the inspection and all applicable related investigative and corrective actions required by paragraph (h) of this AD on an operator’s fleet, the MEL revision specified in paragraph (g) of this AD is no longer required by this AD, and the provisions for relief for the affected MEL items in figure 1 to paragraphs (g) and (i) of this AD may be restored, provided those items are not otherwise restricted by the existing master minimum equipment list (MMEL). daltland on DSKBBV9HB2PROD with RULES (j) Reporting Provisions Although Airbus Alert Operators Transmission A57P011–18, dated October 8, 2018, specifies sending inspection results to Airbus, this AD does not require a report. (k) 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, 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 (l)(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 EASA; or Airbus SAS’s EASA DOA. If approved by VerDate Sep<11>2014 15:57 Nov 07, 2018 Jkt 247001 the DOA, the approval must include the DOA-authorized 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0220, dated October 12, 2018, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0958. (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. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Alert Operators Transmission A57P011–18, dated October 8, 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; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continuedairworthiness.a350@airbus.com; internet https://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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on October 26, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–24391 Filed 11–7–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0934; Product Identifier 2018–NE–35–AD; Amendment 39– 19478; AD 2018–22–05] RIN 2120–AA64 Airworthiness Directives; Engine Alliance Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines with a certain high-pressure turbine (HPT) case installed. This AD requires removal of affected HPT stator cases (HPT cases) from service and their replacement with a part eligible for installation. This AD was prompted by the discovery of a quality escape at a manufacturing facility involving unapproved welds on HPT cases. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective November 23, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications 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 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 Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800–565–0140; email: help24@pw.utc.com; website: www.engineallianceportal.com. You may view this service information at the DATES: E:\FR\FM\08NOR1.SGM 08NOR1 Federal Register / Vol. 83, No. 217 / Thursday, November 8, 2018 / Rules and Regulations 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–2018– 0934. 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–2018– 0934; 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 (phone: 800–647– 5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Matthew Smith, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7735; fax: 781–238–7199; email: matthew.c.smith@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We learned from EA of a quality escape at one of their suppliers, AECC Aero Science and Technology Co., Ltd., which was performing welds on newlymanufactured components to correct errors introduced in their manufacturing process. These welds were not reviewed or approved by either EA or the FAA. EA’s review of manufacturing records determined that these parts include HPT cases installed on EA GP7270, GP7272, 55817 and GP7277 turbofan engines. These HPT cases are life limited. The unapproved repairs reduced the material capability of these HPT cases, which requires their removal prior to reaching their published Airworthiness Limitation Section life limit. This condition, if not addressed, could result in failure of the HPT case, engine fire, and damage to the airplane. We are issuing this AD to address the unsafe condition on these products. FAA’s Justification and Determination of the Effective Date Related Service Information Under 1 CFR Part 51 We reviewed EA Alert Service Bulletin (ASB) EAGP7–A72–401, dated August 23, 2018; and EA Service Bulletin (SB) EAGP7–72–399, dated June 4, 2018. EA ASB EAGP7–A72–401 describes procedures for removing and replacing the affected HPT case, within the identified cycles. EA SB EAGP7–72– 399 describes procedures for removing and replacing the affected HPT case within the specified part cycles since new or part cycles since overhaul. 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. 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, we invite you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2018–0934 and Product Identifier 2018–NE–35–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. We will consider all comments received by the closing date and may amend this final rule because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this final rule. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires removal of the affected HPT cases from service and their replacement with a part eligible for installation. No domestic operators use this product. Therefore, we find good cause that notice and opportunity for prior public comment are unnecessary. In addition, for the reason stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited Costs of Compliance We estimate that this AD affects zero engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Replacement of the HPT case ....................... 20 work-hours × $85 per hour = $1,700 ........ daltland on DSKBBV9HB2PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that VerDate Sep<11>2014 15:57 Nov 07, 2018 Jkt 247001 Parts cost 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, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 $339,400 Cost per product $341,100 Cost on U.S. operators $0 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. E:\FR\FM\08NOR1.SGM 08NOR1 55818 Federal Register / Vol. 83, No. 217 / Thursday, November 8, 2018 / Rules and Regulations 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. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (e) Unsafe Condition This AD was prompted by the discovery of a quality escape at a manufacturing facility performing unapproved welds on HPT cases. We are issuing this AD to prevent failure of the HPT case. The unsafe condition, if not addressed, could result in engine fire and damage to the airplane. (j) Related Information For more information about this AD, contact Matthew Smith, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7735; fax: 781–238–7199; email: matthew.c.smith@faa.gov. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For HPT cases listed in Planning Information, Table 1, of EA ASB EAGP7– A72–401, dated August 23, 2018, remove the affected HPT case from service within the cycles identified in Table 1 of EA SB EAGP7– A72–401 after the effective date of this AD. (2) For HPT cases listed in Planning Information, Table 1, of EAGP7–72–399, dated June 4, 2018, remove the affected HPT cases from service, using the number of part cycles since new (PCSN) or part cycles since overhaul (PCSO), whichever is less, as specified in Table 1 to paragraph (g)(2) of this AD. TABLE 1 TO PARAGRAPH (g)(2) OF THIS AD—COMPLIANCE TIMES Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PCSN or PCSO 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): ■ 2018–22–05 Engine Alliance: Amendment 39–19478; Docket No. FAA–2018–0934; Product Identifier 2018–NE–35–AD. (a) Effective Date This AD is effective November 23, 2018. daltland on DSKBBV9HB2PROD with RULES (b) Affected ADs None. (c) Applicability This AD applies to Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines, with a high-pressure turbine (HPT) stator case (HPT case), part number (P/N) 2060M40G02 or 2137M29G01 installed, and with HPT case serial numbers (S/Ns) listed in Planning Information, Table 1, of EA Alert Service Bulletin (ASB) EAGP7–A72–401, dated August 23, 2018, and in Planning Information, Table 1, of EA Service Bulletin (SB) EAGP7–72–399, dated June 4, 2018. VerDate Sep<11>2014 15:57 Nov 07, 2018 Jkt 247001 Less than 1000 ......... 1001 to 2000 ............. 2001 to 3000 ............. 3001 to 4000 ............. 4001 to 5000 ............. 5001 or more ............ Remove from service within these cycles after the effective date of this AD 150 cycles. 125 cycles. 100 cycles. 75 cycles. 50 cycles. 25 cycles. (3) Replace the removed HPT case with a part eligible for installation before further flight. (h) Definitions For the purpose of this AD, a ‘‘part eligible for installation’’ is any HPT case not identified in paragraph (c) of this AD or an HPT case listed in this AD that has been inspected and repaired by a method approved by the Manager, ECO Branch, FAA. (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, PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Engine Alliance (EA) Alert Service Bulletin EAGP7–A72–401, dated August 23, 2018. (ii) EA Service Bulletin EAGP7–72–399, dated June 4, 2018. (3) For service information identified in this AD, contact Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800– 565–0140; email: help24@pw.utc.com; website: www.engineallianceportal.com. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on November 2, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–24386 Filed 11–7–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 31221; Amdt. No. 3824] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and SUMMARY: E:\FR\FM\08NOR1.SGM 08NOR1

Agencies

[Federal Register Volume 83, Number 217 (Thursday, November 8, 2018)]
[Rules and Regulations]
[Pages 55816-55818]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24386]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0934; Product Identifier 2018-NE-35-AD; Amendment 
39-19478; AD 2018-22-05]
RIN 2120-AA64


Airworthiness Directives; Engine Alliance Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines with a 
certain high-pressure turbine (HPT) case installed. This AD requires 
removal of affected HPT stator cases (HPT cases) from service and their 
replacement with a part eligible for installation. This AD was prompted 
by the discovery of a quality escape at a manufacturing facility 
involving unapproved welds on HPT cases. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective November 23, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications 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 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 
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800-
565-0140; email: [email protected]; website: 
www.engineallianceportal.com. You may view this service information at 
the

[[Page 55817]]

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-2018-0934.

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-2018-
0934; 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 (phone: 
800-647-5527) is listed above. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Matthew Smith, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7735; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We learned from EA of a quality escape at one of their suppliers, 
AECC Aero Science and Technology Co., Ltd., which was performing welds 
on newly-manufactured components to correct errors introduced in their 
manufacturing process. These welds were not reviewed or approved by 
either EA or the FAA. EA's review of manufacturing records determined 
that these parts include HPT cases installed on EA GP7270, GP7272, and 
GP7277 turbofan engines. These HPT cases are life limited. The 
unapproved repairs reduced the material capability of these HPT cases, 
which requires their removal prior to reaching their published 
Airworthiness Limitation Section life limit. This condition, if not 
addressed, could result in failure of the HPT case, engine fire, and 
damage to the airplane. We are issuing this AD to address the unsafe 
condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed EA Alert Service Bulletin (ASB) EAGP7-A72-401, dated 
August 23, 2018; and EA Service Bulletin (SB) EAGP7-72-399, dated June 
4, 2018. EA ASB EAGP7-A72-401 describes procedures for removing and 
replacing the affected HPT case, within the identified cycles. EA SB 
EAGP7-72-399 describes procedures for removing and replacing the 
affected HPT case within the specified part cycles since new or part 
cycles since overhaul. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or by the means identified in the ADDRESSES section.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires removal of the affected HPT cases from service and 
their replacement with a part eligible for installation.

FAA's Justification and Determination of the Effective Date

    No domestic operators use this product. Therefore, we find good 
cause that notice and opportunity for prior public comment are 
unnecessary. In addition, for the reason stated above, we find that 
good cause exists for making this amendment effective in less than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA-2018-
0934 and Product Identifier 2018-NE-35-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

Costs of Compliance

    We estimate that this AD affects zero 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
----------------------------------------------------------------------------------------------------------------
Replacement of the HPT case...........  20 work-hours x $85 per         $339,400        $341,100              $0
                                         hour = $1,700.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 55818]]

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):

2018-22-05 Engine Alliance: Amendment 39-19478; Docket No. FAA-2018-
0934; Product Identifier 2018-NE-35-AD.

(a) Effective Date

    This AD is effective November 23, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Engine Alliance (EA) GP7270, GP7272, and 
GP7277 turbofan engines, with a high-pressure turbine (HPT) stator 
case (HPT case), part number (P/N) 2060M40G02 or 2137M29G01 
installed, and with HPT case serial numbers (S/Ns) listed in 
Planning Information, Table 1, of EA Alert Service Bulletin (ASB) 
EAGP7-A72-401, dated August 23, 2018, and in Planning Information, 
Table 1, of EA Service Bulletin (SB) EAGP7-72-399, dated June 4, 
2018.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by the discovery of a quality escape at a 
manufacturing facility performing unapproved welds on HPT cases. We 
are issuing this AD to prevent failure of the HPT case. The unsafe 
condition, if not addressed, could result in engine fire and damage 
to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For HPT cases listed in Planning Information, Table 1, of EA 
ASB EAGP7-A72-401, dated August 23, 2018, remove the affected HPT 
case from service within the cycles identified in Table 1 of EA SB 
EAGP7-A72-401 after the effective date of this AD.
    (2) For HPT cases listed in Planning Information, Table 1, of 
EAGP7-72-399, dated June 4, 2018, remove the affected HPT cases from 
service, using the number of part cycles since new (PCSN) or part 
cycles since overhaul (PCSO), whichever is less, as specified in 
Table 1 to paragraph (g)(2) of this AD.

        Table 1 to Paragraph (g)(2) of This AD--Compliance Times
------------------------------------------------------------------------
                                             Remove from service within
               PCSN or PCSO                    these cycles after the
                                              effective date of this AD
------------------------------------------------------------------------
Less than 1000............................  150 cycles.
1001 to 2000..............................  125 cycles.
2001 to 3000..............................  100 cycles.
3001 to 4000..............................  75 cycles.
4001 to 5000..............................  50 cycles.
5001 or more..............................  25 cycles.
------------------------------------------------------------------------

    (3) Replace the removed HPT case with a part eligible for 
installation before further flight.

(h) Definitions

    For the purpose of this AD, a ``part eligible for installation'' 
is any HPT case not identified in paragraph (c) of this AD or an HPT 
case listed in this AD that has been inspected and repaired by a 
method approved by the Manager, ECO Branch, FAA.

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

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Engine Alliance (EA) Alert Service Bulletin EAGP7-A72-401, 
dated August 23, 2018.
    (ii) EA Service Bulletin EAGP7-72-399, dated June 4, 2018.
    (3) For service information identified in this AD, contact 
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 
800-565-0140; email: [email protected]; website: 
www.engineallianceportal.com.
    (4) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 2, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-24386 Filed 11-7-18; 8:45 am]
 BILLING CODE 4910-13-P
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