Airworthiness Directives; General Electric Company Turbofan Engines, 9751-9753 [2016-04031]

Download as PDF Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations (ii) Either an ultrasonic inspection or a surface HFEC inspection for cracks (depending on the location of the scribe line(s)) of any skin panel common to a stringer S–14 L/R lap splice between fuselage station 655 and station 1434 that has a scribe line 0.001 inch or deeper. (iii) An external phased array ultrasonic inspection for cracks in the lower/overlapped skin of the stringer S–14 L/R lap splices between fuselage station 655 and station 1434. (iv) An open hole HFEC inspection for skin cracks at the upper and lower fastener rows of the stringer S–14 L/R lap splices. (3) Inspection ‘‘C’’ includes the inspections for scribe lines and cracks specified in paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD on stringer S–14 L/R lap splice between fuselage station 655 and station 1434 on both sides of the airplane. (i) A detailed inspection for scribe lines. If any scribe line is found during the inspection required by this paragraph, the actions include the inspections specified in paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this AD. (A) A detailed inspection for cracks of the scribe line area(s). (B) Either an ultrasonic inspection or a surface HFEC inspection for cracks (depending on the location of the scribe line(s)). (ii) An external phased array ultrasonic inspection for cracks in the lower/overlapped skin of the stringer S–14 L/R lap splices between fuselage station 655 and station 1434. (iii) An open hole HFEC inspection for skin cracks at the upper and lower fastener rows of the stringer S–14 L/R lap splices. (h) Exceptions to Service Information Specifications (1) Where Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time ‘‘after the effective date of this AD.’’ (2) If, during accomplishment of any inspection required by this AD, any condition is found for which Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, specifies to contact Boeing for special repair instructions or supplemental instructions for the modification, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, do the repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD. mstockstill on DSK4VPTVN1PROD with RULES (i) Lap Splice Modification At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014: Do the left-side and rightside lap splice modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, except as provided by paragraph (h)(2) of this AD. VerDate Sep<11>2014 17:33 Feb 25, 2016 Jkt 238001 (j) Post-Modification Inspections and Corrective Action At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014: Do a post-modification internal surface HFEC inspection for skin cracks in the modified lap splices on both sides of the airplane; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, except as provided by paragraph (h)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the modified lap splices thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 ACO, send it to the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information For more information about this AD, contact Eric Lin, Aerospace Engineer, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 9751 Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6412; fax: 425– 917–6590; email: Eric.Lin@faa.gov. (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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin 777– 53A0052, dated October 10, 2014. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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 Renton, Washington, on February 16, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–03886 Filed 2–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2984; Directorate Identifier 2015–NE–21–AD; Amendment 39– 18405; AD 2016–04–11] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx– 1B54, –1B58, –1B64, –1B67, and –1B70 turbofan engine models. This AD was prompted by reports of two separate, single engine in-flight shutdowns SUMMARY: E:\FR\FM\26FER1.SGM 26FER1 9752 Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations (IFSDs) caused by high-pressure turbine (HPT) rotor stage 1 blade failure. This AD requires inspection and conditional removal of affected HPT rotor stage 1 blades. We are issuing this AD to prevent failure of the HPT rotor stage 1 blades, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane. DATES: This AD is effective April 1, 2016. ADDRESSES: 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 & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. mstockstill on DSK4VPTVN1PROD with RULES 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–2015– 2984; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7120; fax: 781– 238–7199; email: chris.mcguire@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all GE GEnx–1B54, –1B58, –1B64, –1B67, and –1B70 turbofan engine models. The NPRM published in the Federal Register on August 27, 2015 (80 FR 51965). The NPRM was prompted by reports of two separate, single engine IFSDs caused by HPT rotor stage 1 blade failure. The NPRM proposed to require inspection and conditional removal of affected HPT rotor stage 1 blades. We are issuing this AD to correct the unsafe condition that VerDate Sep<11>2014 17:33 Feb 25, 2016 Jkt 238001 could result in failure of the HPT rotor stage 1 blades, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Support for the NPRM The National Transportation Safety Board (NTSB) expressed support for the NPRM (80 FR 51965). Request To Change Applicability United Airlines (United) requested that the Applicability paragraph be changed to more appropriately address engine models. United stated that the GEnx–1B54 and GEnx–1B58 be removed and GEnx–1B64G03, 1B64G04, 1B67G03, 1B67G04, 1B70G03 and 1B70G04 be added to paragraph (c) Applicability. United indicated this change would improve clarity and accomplishment of the AD. We disagree. This AD applies to all GE GEnx–1B54, –1B58, –1B64, –1B67, and –1B70 turbofan engine models, as listed in the GEnx type certificate data sheet. We did not change this AD. Request To Change Compliance United requested that the Compliance paragraph be changed to clarify maintenance actions. United requested that in paragraph (e) the phrase, ‘‘ . . . remove the cracked blade’’ be changed to read, ‘‘ . . . remove the engine containing the cracked blade.’’ United reasoned that removing the cracked blade is not a maintenance option. We partially agree. We agree with changing the compliance language to include disposition of a cracked blade. We disagree with using the phrase, ‘‘ . . . remove the engine containing the cracked blade’’ because removal of the cracked blade addresses the unsafe condition. We revised paragraphs (e)(1)(i) and (e)(1)(ii) of this AD to include, ‘‘ . . . remove the cracked blade from service. . . .’’ Request To Change the Summary and Unsafe Condition Boeing and General Electric Company (GE) requested that the Summary and Unsafe Condition paragraphs be clarified to reflect that two separate, single engine IFSDs occurred, prompting the need for this AD. We agree. We changed the Summary and Unsafe Condition paragraphs of this PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 AD to read: ‘‘This AD was prompted by reports of two separate, single engine inflight shutdowns, caused by HPT rotor stage 1 blade failure. . . .’’ Request To Change the Cost of Compliance Boeing requested that the Costs of Compliance paragraph specifically state that the projected costs are for only the initial inspection and not for repetitive inspections. Boeing indicated this is needed to clarify the cost of compliance. We agree. We changed the Costs of Compliance paragraph of this AD to include, ‘‘We also estimate that it will take about 1 hour per engine to comply with the initial inspection in this AD.’’ Request To Change Compliance Time Japan Airlines (JAL) and GE suggested that in paragraph (e)(1) Compliance, the need to inspect within 1,000 cycles since new (CSN) may not be representative of the fleet. We disagree. The initial blade inspection compliance time was based on the safety evaluation of the known failures. Any person may make a request for an Alternative Method of Compliance (AMOC) to the compliance times of this AD using the procedures listed herein. We did not change this AD. Request To Change Compliance GE requested that the Compliance paragraph be changed to clarify that the criteria of multiple cracks should be based on an individual blade and not multiple blades, each with a single crack. We agree. We changed paragraph (e)(1)(i) of this AD to read: ‘‘. . . , or if more than one axial crack of any length is found on one blade, remove the cracked blade from service before further flight.’’ Revision to Service Information We revised the service information in the Related Information section of this AD to Revision 01 of GE GEnx–1B Service Bulletin (SB) No. 72–0267 R01, dated August 10, 2015. GE made an editorial change to this SB that did not affect its contents. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 51965) for correcting the unsafe condition; and E:\FR\FM\26FER1.SGM 26FER1 Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 51965). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD will affect 4 engines installed on airplanes of U.S. registry. We also estimate that it will take about 1 hour per engine to comply with the initial inspection in this AD. The average labor rate is $85 per hour. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $340. mstockstill on DSK4VPTVN1PROD 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. 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 to the extent that it justifies making a regulatory distinction, 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. VerDate Sep<11>2014 17:33 Feb 25, 2016 Jkt 238001 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): ■ 9753 0.2 inch, inspect the cracked blade within 50 blade cycles since last inspection (CSLI). (iv) If an axial crack is found with a length less than 0.1 inch, inspect the cracked blade within 100 blade CSLI. (v) If no cracks were found, perform a BSI of the blades within 125 blade CSLI. (2) Thereafter, perform a repetitive BSI of the convex surface of the HPT rotor stage 1 blades for axial cracks from the platform to 30% span within 125 blade CSLI and disposition as specified in paragraphs (e)(1)(i) through (e)(1)(v) of this AD, or remove the blades from service. (f) Definition For the purpose of this AD, a ‘‘blade cycle’’ is defined as the number of engine cycles that a set of rotor blades has accrued, regardless of the engine(s) in which they have operated. (g) Alternative Methods of Compliance (AMOCs) 2016–04–11 General Electric Company: Amendment 39–18405; Docket No. FAA–2015–2984; Directorate Identifier 2015–NE–21–AD. The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (a) Effective Date This AD is effective April 1, 2016. (h) Related Information (b) Affected ADs None. (c) Applicability This AD applies to all General Electric Company (GE) GEnx–1B54, –1B58, –1B64, –1B67, and –1B70 turbofan engine models with high-pressure turbine (HPT) rotor stage 1 blade, part number 2305M26P06, installed. (d) Unsafe Condition This AD was prompted by reports of two separate, single engine in-flight shutdowns, caused by HPT rotor stage 1 blade failure. We are issuing this AD to prevent failure of the HPT rotor stage 1 blades, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Perform an initial borescope inspection (BSI) of the convex surface of the HPT rotor stage 1 blades for axial cracks from the platform to 30% span, within 1,000 blade cycles since new or 25 cycles after the effective date of this AD, whichever occurs later, and disposition as follows: (i) If any axial crack with a length greater than or equal to 0.3 inch is found, or if any axial crack of any length turning in a radial direction is found, or if more than one axial crack of any length is found on one blade, remove the cracked blade from service before further flight. (ii) If an axial crack is found with a length greater than or equal to 0.2 inch and less than 0.3 inch, remove the cracked blade from service within 10 blade cycles. (iii) If an axial crack is found with a length greater than or equal to 0.1 inch and less than PO 00000 Frm 00013 Fmt 4700 Sfmt 9990 (1) For more information about this AD, contact Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7120; fax: 781–238–7199; email: chris.mcguire@faa.gov. (2) GE GEnx–1B Service Bulletin No. 72– 0267 R01, dated August 10, 2015 can be obtained from GE using the contact information in paragraph (h)(3) of this AD. (3) For 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 the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on February, 18, 2016. Ann C. Mollica, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–04031 Filed 2–25–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\26FER1.SGM 26FER1

Agencies

[Federal Register Volume 81, Number 38 (Friday, February 26, 2016)]
[Rules and Regulations]
[Pages 9751-9753]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04031]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2984; Directorate Identifier 2015-NE-21-AD; 
Amendment 39-18405; AD 2016-04-11]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 
turbofan engine models. This AD was prompted by reports of two 
separate, single engine in-flight shutdowns

[[Page 9752]]

(IFSDs) caused by high-pressure turbine (HPT) rotor stage 1 blade 
failure. This AD requires inspection and conditional removal of 
affected HPT rotor stage 1 blades. We are issuing this AD to prevent 
failure of the HPT rotor stage 1 blades, which could lead to failure of 
one or more engines, loss of thrust control, and damage to the 
airplane.

DATES: This AD is effective April 1, 2016.

ADDRESSES: 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 & Propeller Directorate, 1200 District Avenue, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call 781-238-7125.

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-2015-
2984; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Christopher McGuire, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7120; fax: 781-238-7199; email: chris.mcguire@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all GE GEnx-1B54, -1B58, -
1B64, -1B67, and -1B70 turbofan engine models. The NPRM published in 
the Federal Register on August 27, 2015 (80 FR 51965). The NPRM was 
prompted by reports of two separate, single engine IFSDs caused by HPT 
rotor stage 1 blade failure. The NPRM proposed to require inspection 
and conditional removal of affected HPT rotor stage 1 blades. We are 
issuing this AD to correct the unsafe condition that could result in 
failure of the HPT rotor stage 1 blades, which could lead to failure of 
one or more engines, loss of thrust control, and damage to the 
airplane.

Comments

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

Support for the NPRM

    The National Transportation Safety Board (NTSB) expressed support 
for the NPRM (80 FR 51965).

Request To Change Applicability

    United Airlines (United) requested that the Applicability paragraph 
be changed to more appropriately address engine models. United stated 
that the GEnx-1B54 and GEnx-1B58 be removed and GEnx-1B64G03, 1B64G04, 
1B67G03, 1B67G04, 1B70G03 and 1B70G04 be added to paragraph (c) 
Applicability. United indicated this change would improve clarity and 
accomplishment of the AD.
    We disagree. This AD applies to all GE GEnx-1B54, -1B58, -1B64, -
1B67, and -1B70 turbofan engine models, as listed in the GEnx type 
certificate data sheet. We did not change this AD.

Request To Change Compliance

    United requested that the Compliance paragraph be changed to 
clarify maintenance actions. United requested that in paragraph (e) the 
phrase, `` . . . remove the cracked blade'' be changed to read, `` . . 
. remove the engine containing the cracked blade.'' United reasoned 
that removing the cracked blade is not a maintenance option.
    We partially agree. We agree with changing the compliance language 
to include disposition of a cracked blade. We disagree with using the 
phrase, `` . . . remove the engine containing the cracked blade'' 
because removal of the cracked blade addresses the unsafe condition.
    We revised paragraphs (e)(1)(i) and (e)(1)(ii) of this AD to 
include, `` . . . remove the cracked blade from service. . . .''

Request To Change the Summary and Unsafe Condition

    Boeing and General Electric Company (GE) requested that the Summary 
and Unsafe Condition paragraphs be clarified to reflect that two 
separate, single engine IFSDs occurred, prompting the need for this AD.
    We agree. We changed the Summary and Unsafe Condition paragraphs of 
this AD to read: ``This AD was prompted by reports of two separate, 
single engine in-flight shutdowns, caused by HPT rotor stage 1 blade 
failure. . . .''

Request To Change the Cost of Compliance

    Boeing requested that the Costs of Compliance paragraph 
specifically state that the projected costs are for only the initial 
inspection and not for repetitive inspections. Boeing indicated this is 
needed to clarify the cost of compliance.
    We agree. We changed the Costs of Compliance paragraph of this AD 
to include, ``We also estimate that it will take about 1 hour per 
engine to comply with the initial inspection in this AD.''

Request To Change Compliance Time

    Japan Airlines (JAL) and GE suggested that in paragraph (e)(1) 
Compliance, the need to inspect within 1,000 cycles since new (CSN) may 
not be representative of the fleet.
    We disagree. The initial blade inspection compliance time was based 
on the safety evaluation of the known failures. Any person may make a 
request for an Alternative Method of Compliance (AMOC) to the 
compliance times of this AD using the procedures listed herein. We did 
not change this AD.

Request To Change Compliance

    GE requested that the Compliance paragraph be changed to clarify 
that the criteria of multiple cracks should be based on an individual 
blade and not multiple blades, each with a single crack.
    We agree. We changed paragraph (e)(1)(i) of this AD to read: ``. . 
. , or if more than one axial crack of any length is found on one 
blade, remove the cracked blade from service before further flight.''

Revision to Service Information

    We revised the service information in the Related Information 
section of this AD to Revision 01 of GE GEnx-1B Service Bulletin (SB) 
No. 72-0267 R01, dated August 10, 2015. GE made an editorial change to 
this SB that did not affect its contents.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously. We have determined that 
these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 51965) for correcting the unsafe condition; and

[[Page 9753]]

     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 51965).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD will affect 4 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
hour per engine to comply with the initial inspection in this AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the total cost of this AD to U.S. operators to be $340.

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.

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 to the extent 
that it justifies making a regulatory distinction, 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):

2016-04-11 General Electric Company: Amendment 39-18405; Docket No. 
FAA-2015-2984; Directorate Identifier 2015-NE-21-AD.

(a) Effective Date

    This AD is effective April 1, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all General Electric Company (GE) GEnx-1B54, 
-1B58, -1B64, -1B67, and -1B70 turbofan engine models with high-
pressure turbine (HPT) rotor stage 1 blade, part number 2305M26P06, 
installed.

(d) Unsafe Condition

    This AD was prompted by reports of two separate, single engine 
in-flight shutdowns, caused by HPT rotor stage 1 blade failure. We 
are issuing this AD to prevent failure of the HPT rotor stage 1 
blades, which could lead to failure of one or more engines, loss of 
thrust control, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Perform an initial borescope inspection (BSI) of the convex 
surface of the HPT rotor stage 1 blades for axial cracks from the 
platform to 30% span, within 1,000 blade cycles since new or 25 
cycles after the effective date of this AD, whichever occurs later, 
and disposition as follows:
    (i) If any axial crack with a length greater than or equal to 
0.3 inch is found, or if any axial crack of any length turning in a 
radial direction is found, or if more than one axial crack of any 
length is found on one blade, remove the cracked blade from service 
before further flight.
    (ii) If an axial crack is found with a length greater than or 
equal to 0.2 inch and less than 0.3 inch, remove the cracked blade 
from service within 10 blade cycles.
    (iii) If an axial crack is found with a length greater than or 
equal to 0.1 inch and less than 0.2 inch, inspect the cracked blade 
within 50 blade cycles since last inspection (CSLI).
    (iv) If an axial crack is found with a length less than 0.1 
inch, inspect the cracked blade within 100 blade CSLI.
    (v) If no cracks were found, perform a BSI of the blades within 
125 blade CSLI.
    (2) Thereafter, perform a repetitive BSI of the convex surface 
of the HPT rotor stage 1 blades for axial cracks from the platform 
to 30% span within 125 blade CSLI and disposition as specified in 
paragraphs (e)(1)(i) through (e)(1)(v) of this AD, or remove the 
blades from service.

(f) Definition

    For the purpose of this AD, a ``blade cycle'' is defined as the 
number of engine cycles that a set of rotor blades has accrued, 
regardless of the engine(s) in which they have operated.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: ANE-AD-AMOC@faa.gov.

(h) Related Information

    (1) For more information about this AD, contact Christopher 
McGuire, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 
01803; phone: 781-238-7120; fax: 781-238-7199; email: 
chris.mcguire@faa.gov.
    (2) GE GEnx-1B Service Bulletin No. 72-0267 R01, dated August 
10, 2015 can be obtained from GE using the contact information in 
paragraph (h)(3) of this AD.
    (3) For 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 the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on February, 18, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04031 Filed 2-25-16; 8:45 am]
BILLING CODE 4910-13-P
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