Airworthiness Directives; General Electric Company Turbofan Engines, 36724-36727 [2018-16309]

Download as PDF 36724 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same novel or unusual design feature, or should any other model already included on the same type certificate be modified to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the Bombardier Model BD– 700–2A12 and BD–700–2A13 series airplanes must comply with the fuelvent and exhaust-emission requirements of 14 CFR part 34, and the noisecertification requirements of 14 CFR part 36. The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type certification basis under § 21.101. daltland on DSKBBV9HB2PROD with RULES Novel or Unusual Design Features The Model BD–700–2A12 and BD– 700–2A13 series airplanes will incorporate the following novel or unusual design features: Fly-by-wire EFCS that will limit pitch and roll functions to prevent the airplane from attaining certain pitch attitudes and roll angles greater than plus or minus 65 degrees, and introduce positive spiral stability introduced for roll angles greater than 30 degrees at speeds below VMO/MMO. This system generates the actual surface commands that provide for stability augmentation and flight control for all three airplane axes (longitudinal, lateral, and directional). Discussion Part 25 of title 14 of the CFR does not specifically relate to flight characteristics associated with fixed attitude limits. Bombardier proposes to implement on the airplanes pitch and roll attitude-limiting functions via the EFCS normal mode. This will prevent the airplane from attaining certain pitch attitudes and roll angles greater than plus or minus 65 degrees. In addition, positive spiral stability, introduced for roll angles greater than 30 degrees at speeds below VMO/MMO, and spiral stability characteristics, must not require excessive pilot strength to achieve bank angles up to the bankangle limit. Bombardier requested this amendment, in order to be performancebased rather than prescriptive and to more closely follow the language VerDate Sep<11>2014 16:21 Jul 30, 2018 Jkt 244001 developed in the Aviation Rulemaking Advisory Committee (ARAC) Flight Test Harmonization Working Group (FTHWG). The FAA concurs with this request. The basic envelope protection requirement, historically applied, is to not unduly limit the maneuver capability of the airplane, or interfere with its ability to perform maneuvers required for normal and emergency operations. Since the design details used to meet this requirement vary from airplane to airplane, this amendment recognizes and adopts that philosophy for this specific design implementation. The substance of the special conditions is unchanged, in that, for this specific design, the design details support the objective of not unduly limiting the maneuver capability, while also protecting the airplane from adverse attitudes. These special conditions are in addition to the requirements of § 25.143. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. Applicability As discussed above, these special conditions are applicable to the Model BD–700–2A12 and BD–700–2A13 series airplanes. Should Bombardier apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one model series of airplanes. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. Authority Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702, 44704. The Special Conditions PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Issued in Des Moines, Washington. Victor Wicklund, Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2018–16360 Filed 7–30–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0630; Product Identifier 2018–NE–25–AD; Amendment 39– 19347; AD 2018–16–07] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Bombardier Model BD–700– 2A12 and BD–700–2A13 series airplanes: In addition to § 25.143, the following requirements apply to the electronic ■ flight-control system (EFCS) pitch- and roll-limiting functions: 1. The pitch-limiting function must not impede normal maneuvering for pitch angles up to the maximum required for normal maneuvering, including a normal, all-enginesoperating takeoff, plus a suitable margin to allow for satisfactory speed control. 2. The pitch- and roll-limiting functions must not restrict or prevent attaining pitch attitudes necessary for emergency maneuvering, or roll angles up to 65 degrees. Spiral stability, which is introduced above 30 degrees of roll angle, must not require excessive pilot strength to achieve these roll angles. Other protections, which further limit the roll capability under certain extreme angle-of-attack, attitude, or high-speed conditions, are acceptable, as long as the airplane is able to perform coordinated turns as per § 25.143(h). A roll attitude limit of approximately 45 degrees at high angle-of-attack conditions is acceptable. 3. A reduced roll attitude limit is acceptable at extreme nose down pitch attitudes and beyond the overspeed warning to provide protection against high-speed combined pitch and roll upsets. The airplane should be able to perform operational turns at these speeds. A roll attitude limit of approximately 30 degrees at Vdf/Mdf is considered acceptable. We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx– 1B54, –1B58, –1B64, –1B67, –1B70, –1B54/P1, –1B58/P1, –1B64/P1, –1B67/ SUMMARY: E:\FR\FM\31JYR1.SGM 31JYR1 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations daltland on DSKBBV9HB2PROD with RULES P1, –1B70/P1, –1B54/P2, –1B58/P2, –1B64/P2, –1B67/P2, –1B70/P2, –1B70C/P1, –1B70/72/P1, –1B70/75/P1, –1B74/75/P1, –1B75/P1, –1B70C/P2, –1B70/72/P2, –1B70/75/P2, –1B74/75/ P2, –1B75/P2, –1B76/P2, –1B76A/P2, –1B78/P2, –2B67, –2B67B, and –2B67/P turbofan engines. This AD requires removal of affected highpressure turbine (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. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 15, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 15, 2018. We must receive comments on this AD by September 14, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: aviation.fleetsupport@ge.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 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– 0630. 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– 0630; or in person at Docket Operations VerDate Sep<11>2014 16:21 Jul 30, 2018 Jkt 244001 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: Herman Mak, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7147; fax: 781–238–7199; email: herman.mak@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We learned from GE of a quality escape at one of their suppliers. This supplier was performing welds on newly-manufactured components to correct errors introduced in their manufacturing process. These welds were not reviewed or approved by either GE or the FAA. GE’s review of manufacturing records determined that these parts include HPT cases installed on GEnx engines. These HPT cases are life limited. The unapproved repairs reduced the material capability of these 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 GE Service Bulletin (SB) GEnx–1B S/B 72–0424, Revision 03, dated June 29, 2018 and GEnx–2B S/B 72–0360, Revision 03, dated June 29, 2018. The SBs describe procedures for removing the affected HPT cases from the engine. GE SB GEnx–1B S/B 72– 0424 is effective for GEnx–1B engines with the serial numbers of HPT cases listed in that SB. GE SB GEnx–2B S/B 72–0360 is effective for GEnx-2B engines with the serial numbers of HPT cases listed in that SB. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Other Related Service Information We reviewed Inspection 001, Subtask 72–52–01–230–001 of GEnx–1B Cleaning, Inspection, and Repair Manual GEK112862, Rev 27, dated April 30, 2018, and GEnx–2B Cleaning, Inspection, and Repair Manual PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 36725 GEK114120, Rev 20, dated April 30, 2018. These manuals provide guidance for conducting Class A fluorescent penetrant inspections. 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 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 because the compliance time for the required action is shorter than the time necessary for the public to comment and for us to publish the final rule. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. 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–2018–0630 and Product Identifier 2018–NE–25–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. We will consider all comments received by the closing date and may amend this final rule because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this final rule. E:\FR\FM\31JYR1.SGM 31JYR1 36726 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations Costs of Compliance We estimate the following costs to comply with this AD: We estimate that this AD affects 13 engines installed on airplanes of U.S. registry. ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Replacement of HPT case .............................. 0 work-hours × $85 per hour = $0 ................. $362,400 $362,400 $4,711,200 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 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. VerDate Sep<11>2014 16:21 Jul 30, 2018 Jkt 244001 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 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): ■ 2018–16–07 General Electric Company: Amendment 39–19347; Docket No. FAA–2018–0630; Product Identifier 2018–NE–25–AD. (a) Effective Date This AD is effective August 15, 2018. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) GEnx–1B54, –1B58, –1B64, PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 –1B67, –1B70, –1B54/P1, –1B58/P1, –1B64/ P1, –1B67/P1, –1B70/P1, –1B54/P2, –1B58/ P2, –1B64/P2, –1B67/P2, –1B70/P2, –1B70C/ P1, –1B70/72/P1, –1B70/75/P1, –1B74/75/P1, –1B75/P1, –1B70C/P2, –1B70/72/P2, –1B70/ 75/P2, –1B74/75/P2, –1B75/P2, –1B76/P2, –1B76A/P2, –1B78/P2, –2B67, –2B67B, and –2B67/P turbofan engines with a highpressure turbine (HPT) stator case (HPT case), part number (P/N) 2302M90G04 installed, and with any serial number (S/N) listed in Table 1, 2, or 3, in the Planning Information section of GE Service Bulletin (SB) GEnx–2B S/B 72–0360, Revision 03, dated June 29, 2018, or GEnx–1B S/B 72– 0424, Revision 03, dated June 29, 2018, installed. (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 involving 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 or 2, of GE SBs GEnx– 2B S/B 72–0360, Revision 03, dated June 29, 2018 and GEnx–1B S/B 72–0424, Revision 03, dated June 29, 2018, determine the lesser of the following: Cycles since new (CSN) or cycles since Class A fluorescent penetrant inspection (CSFPI) of the entire HPT case. (2) Using the determination made in paragraph (g)(1) of this AD, remove from service the HPT case after the effective date of this AD as specified in Table 1 to paragraph (g) of this AD. Replace the removed HPT case with a part eligible for installation. E:\FR\FM\31JYR1.SGM 31JYR1 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations (h) Installation Prohibition (1) After the effective date of this AD, do not install any affected HPT case onto any engine. (2) After the effective date of this AD, HPT cases listed in Planning Information, Table 3, in GE SB GEnx–2B S/B 72–0360, Revision 03, dated June 29, 2018 or GEnx–1B S/B 72– 0424, Revision 03, dated June 29, 2018, and any higher level assemblies with these parts installed, may not be removed from a GEnx– 2B engine and installed on a GEnx–1B engine or removed from a GEnx–1B engine and installed on a GEnx–2B engine. (i) Alternative Methods of Compliance (AMOCs) daltland on DSKBBV9HB2PROD with RULES (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. You may email your request to: ANE-AD-AMOC@ faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (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) General Electric Company (GE) Service Bulletin (SB) GEnx–2B S/B 72–0360, Revision 03, dated June 29, 2018. (ii) GE SB GEnx–1B S/B 72–0424, Revision 03, dated June 29, 2018. (3) For GE service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: aviation.fleetsupport@ge.com. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on July 25, 2018. Karen M. Grant, Acting Manager, Engine & Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–16309 Filed 7–30–18; 8:45 am] BILLING CODE 4910–13–P For more information about this AD, contact Herman Mak, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7147; fax: 781–238–7199; email: herman.mak@faa.gov. 16:21 Jul 30, 2018 Jkt 244001 PO 00000 Federal Energy Regulatory Commission 18 CFR Part 40 [Docket No. RM18–2–000; Order No. 848] Cyber Security Incident Reporting Reliability Standards Federal Energy Regulatory Commission. ACTION: Final rule. AGENCY: The Federal Energy Regulatory Commission (Commission) directs the North American Electric Reliability Corporation (NERC) to develop and submit modifications to the NERC Reliability Standards to augment the mandatory reporting of Cyber Security Incidents, including incidents that might facilitate subsequent efforts to harm the reliable operation of the bulk electric system (BES). DATES: This rule will become effective October 1, 2018. FOR FURTHER INFORMATION CONTACT: Margaret Steiner (Technical Information), Office of Electric Reliability, Federal Energy Regulatory Commission, 888 First Street NE, Washington, DC 20426, (202) 502–6704, Margaret.Steiner@ferc.gov. Kevin Ryan (Legal Information), Office of the General Counsel, Federal Energy Regulatory Commission, 888 First Street NE, Washington, DC 20426, (202) 502–6840, Kevin.Ryan@ferc.gov. SUPPLEMENTARY INFORMATION: SUMMARY: Order No. 848—Final Rule (Issued July 19, 2018) 1. Pursuant to section 215(d)(5) of the Federal Power Act (FPA), the Commission directs the North American Electric Reliability Corporation (NERC) to develop and submit modifications to (j) Related Information VerDate Sep<11>2014 DEPARTMENT OF ENERGY Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\31JYR1.SGM 31JYR1 ER31JY18.000</GPH> (3) Remove from service HPT cases listed in Planning Information, Table 3, of GE SBs GEnx–2B S/B 72–0360, Revision 03, dated June 29, 2018 or GEnx–1B S/B 72–0424, Revision 03, dated June 29, 2018, prior to exceeding 10 cycles after the effective date of this AD or exceeding the CSN limits listed in Table 3, whichever comes later. Replace the removed HPT case with a part eligible for installation. 36727

Agencies

[Federal Register Volume 83, Number 147 (Tuesday, July 31, 2018)]
[Rules and Regulations]
[Pages 36724-36727]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16309]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0630; Product Identifier 2018-NE-25-AD; Amendment 
39-19347; AD 2018-16-07]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -
1B54/P1, -1B58/P1, -1B64/P1, -1B67/

[[Page 36725]]

P1, -1B70/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/
P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B70C/P2, -1B70/
72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/
P2, -2B67, -2B67B, and -2B67/P turbofan engines. This AD requires 
removal of affected high-pressure turbine (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. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective August 15, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 15, 
2018.
    We must receive comments on this AD by September 14, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected]. You may view this service information at 
the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, 
Burlington, MA. 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-2018-0630.

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-
0630; 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: Herman Mak, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7147; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We learned from GE of a quality escape at one of their suppliers. 
This supplier was performing welds on newly-manufactured components to 
correct errors introduced in their manufacturing process. These welds 
were not reviewed or approved by either GE or the FAA. GE's review of 
manufacturing records determined that these parts include HPT cases 
installed on GEnx engines. These HPT cases are life limited. The 
unapproved repairs reduced the material capability of these 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 GE Service Bulletin (SB) GEnx-1B S/B 72-0424, Revision 
03, dated June 29, 2018 and GEnx-2B S/B 72-0360, Revision 03, dated 
June 29, 2018. The SBs describe procedures for removing the affected 
HPT cases from the engine. GE SB GEnx-1B S/B 72-0424 is effective for 
GEnx-1B engines with the serial numbers of HPT cases listed in that SB. 
GE SB GEnx-2B S/B 72-0360 is effective for GEnx-2B engines with the 
serial numbers of HPT cases listed in that SB. This service information 
is reasonably available because the interested parties have access to 
it through their normal course of business or by the means identified 
in the ADDRESSES section.

Other Related Service Information

    We reviewed Inspection 001, Subtask 72-52-01-230-001 of GEnx-1B 
Cleaning, Inspection, and Repair Manual GEK112862, Rev 27, dated April 
30, 2018, and GEnx-2B Cleaning, Inspection, and Repair Manual 
GEK114120, Rev 20, dated April 30, 2018. These manuals provide guidance 
for conducting Class A fluorescent penetrant inspections.

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

    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 
because the compliance time for the required action is shorter than the 
time necessary for the public to comment and for us to publish the 
final rule. Therefore, we find good cause that notice and opportunity 
for prior public comment are impracticable. 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-
0630 and Product Identifier 2018-NE-25-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

[[Page 36726]]

Costs of Compliance

    We estimate that this AD affects 13 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 HPT case...........  0 work-hours x $85 per           $362,400         $362,400       $4,711,200
                                     hour = $0.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2018-16-07 General Electric Company: Amendment 39-19347; Docket No. 
FAA-2018-0630; Product Identifier 2018-NE-25-AD.

(a) Effective Date

    This AD is effective August 15, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) GEnx-1B54, -
1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -
1B70/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/
P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B70C/P2, -
1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, 
-1B78/P2, -2B67, -2B67B, and -2B67/P turbofan engines with a high-
pressure turbine (HPT) stator case (HPT case), part number (P/N) 
2302M90G04 installed, and with any serial number (S/N) listed in 
Table 1, 2, or 3, in the Planning Information section of GE Service 
Bulletin (SB) GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018, 
or GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018, installed.

(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 involving 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 or 2, 
of GE SBs GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018 and 
GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018, determine the 
lesser of the following: Cycles since new (CSN) or cycles since 
Class A fluorescent penetrant inspection (CSFPI) of the entire HPT 
case.
    (2) Using the determination made in paragraph (g)(1) of this AD, 
remove from service the HPT case after the effective date of this AD 
as specified in Table 1 to paragraph (g) of this AD. Replace the 
removed HPT case with a part eligible for installation.

[[Page 36727]]

[GRAPHIC] [TIFF OMITTED] TR31JY18.000

    (3) Remove from service HPT cases listed in Planning 
Information, Table 3, of GE SBs GEnx-2B S/B 72-0360, Revision 03, 
dated June 29, 2018 or GEnx-1B S/B 72-0424, Revision 03, dated June 
29, 2018, prior to exceeding 10 cycles after the effective date of 
this AD or exceeding the CSN limits listed in Table 3, whichever 
comes later. Replace the removed HPT case with a part eligible for 
installation.

(h) Installation Prohibition

    (1) After the effective date of this AD, do not install any 
affected HPT case onto any engine.
    (2) After the effective date of this AD, HPT cases listed in 
Planning Information, Table 3, in GE SB GEnx-2B S/B 72-0360, 
Revision 03, dated June 29, 2018 or GEnx-1B S/B 72-0424, Revision 
03, dated June 29, 2018, and any higher level assemblies with these 
parts installed, may not be removed from a GEnx-2B engine and 
installed on a GEnx-1B engine or removed from a GEnx-1B engine and 
installed on a GEnx-2B engine.

(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 Herman Mak, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7147; 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) General Electric Company (GE) Service Bulletin (SB) GEnx-2B 
S/B 72-0360, Revision 03, dated June 29, 2018.
    (ii) GE SB GEnx-1B S/B 72-0424, Revision 03, dated June 29, 
2018.
    (3) For GE service information identified in this AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected].
    (4) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 
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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on July 25, 2018.
Karen M. Grant,
Acting Manager, Engine & Propeller Standards Branch, Aircraft 
Certification Service.
[FR Doc. 2018-16309 Filed 7-30-18; 8:45 am]
 BILLING CODE 4910-13-P