Airworthiness Directives; General Electric Company Turbofan Engines, 70925-70928 [2016-24795]

Download as PDF Federal Register / Vol. 81, No. 199 / Friday, October 14, 2016 / Rules and Regulations Qinfiltration_83 = Qs_83 + Q 83 Where: Qinfiltration_95 and Qinfiltration_83 = total infiltration air heat in cooling mode, calculated at the 95 °F and 83 °F drybulb outdoor conditions in Table 1 of this appendix, in Btu/h. Qs_95 and Qs_83 = sensible heat added to the room by infiltration air, calculated at the 95 °F and 83 °F dry-bulb outdoor conditions in Table 1 of this appendix, in Btu/h. Ql_95 and Ql_83 = latent heat added to the room by infiltration air, calculated at the 95 °F and 83 °F dry-bulb outdoor conditions in Table 1 of this appendix, in Btu/h. * * * * * [FR Doc. 2016–24869 Filed 10–13–16; 8:45 am] BILLING CODE 6450–01–P FARM CREDIT ADMINISTRATION 12 CFR Chapter VI Farm Credit Administration Board Policy Statements Farm Credit Administration. Notice of policy statements and AGENCY: ACTION: index. The Farm Credit Administration (FCA), as part of its annual public notification process, is publishing for notice an index of the 18 Board policy statements currently in existence. Most of the policy statements remain unchanged since our last Federal Register notice on November 2, 2015, except for one as discussed below on Equal Employment Opportunity and Diversity. DATES: October 14, 2016. FOR FURTHER INFORMATION CONTACT: Dale L. Aultman, Secretary to Board, Farm Credit Administration, 1501 Farm Credit Drive, McLean, Virginia 22102–5090, (703) 883–4009, TTY (703) 883–4056; or Mary Alice Donner, Senior Counsel, Office of General Counsel, Farm Credit Administration, 1501 Farm Credit Drive, McLean, Virginia 22102–5090, (703) 883–4020, TTY (703) 883–4020. SUPPLEMENTARY INFORMATION: A list of the 18 FCA Board policy statements is set forth below. FCA Board policy statements may be viewed online at www.fca.gov/handbook.nsf. On August 8, 2016, the FCA Board updated FCA–PS–62 on, ‘‘Equal Employment Opportunity and Diversity.’’ The policy was published in the Federal Register on August 12, 2016 (81 FR 53482). The policy was slightly edited at the Equal Employment ehiers on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 13:00 Oct 13, 2016 Jkt 241001 70925 Opportunity Commission’s recommendation to indicate that FCA begins prompt, thorough, and impartial investigations within 10 days of receiving notice of harassment allegations. The FCA will continue to publish new or revised policy statements in their full text. DEPARTMENT OF TRANSPORTATION FCA Board Policy Statements Airworthiness Directives; General Electric Company Turbofan Engines FCA–PS–34 Disclosure of the Issuance and Termination of Enforcement Documents FCA–PS–37 Communications During Rulemaking FCA–PS–41 Alternative Means of Dispute Resolution FCA–PS–44 Travel FCA–PS–53 Examination Philosophy FCA–PS–59 Regulatory Philosophy FCA–PS–62 Equal Employment Opportunity and Diversity FCA–PS–64 Rules for the Transaction of Business of the Farm Credit Administration Board FCA–PS–65 Release of Consolidated Reporting System Information FCA–PS–67 Nondiscrimination on the Basis of Disability in Agency Programs and Activities FCA–PS–68 FCS Building Association Management Operations Policies and Practices FCA–PS–71 Disaster Relief Efforts by Farm Credit Institutions FCA–PS–72 Financial Institution Rating System (FIRS) FCA–PS–77 Borrower Privacy FCA–PS–78 Official Names of Farm Credit Institutions FCA–PS–79 Consideration and Referral of Supervisory Strategies and Enforcement Actions FCA–PS–80 Cooperative Operating Philosophy—Serving the Members of Farm Credit System Institutions FCA–PS–81 Ethics, Independence, Arm’s-Length Role, Ex Parte Communications and Open Government Dated: October 6, 2016. Dale L. Aultman, Secretary, Farm Credit Administration Board. [FR Doc. 2016–24680 Filed 10–13–16; 8:45 am] BILLING CODE 6705–01–P PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5872; Directorate Identifier 2016–NE–11–AD; Amendment 39– 18681; AD 2016–20–15] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx– 1B64/P2, –1B67/P2, –1B70/P2, –1B70C/ P2, –1B70/75/P2, and –1B74/75/P2 turbofan engines with engine assembly, part number (P/N) 2447M10G01 or P/N 2447M10G02, installed. This AD was prompted by a report of a significant fan rub event. This AD requires rework of the engine fan stator module assembly. We are issuing this AD to prevent failure of the fan blades and the load reduction device, loss of power to one or more engines, loss of thrust control, and loss of the airplane. DATES: This AD is effective November 18, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 18, 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 referenced 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. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5872. SUMMARY: 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–2016– 5872; 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 E:\FR\FM\14OCR1.SGM 14OCR1 70926 Federal Register / Vol. 81, No. 199 / Friday, October 14, 2016 / Rules and Regulations 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–1B64/P2, –1B67/ P2, –1B70/P2, –1B70C/P2, –1B70/75/P2, and –1B74/75/P2 turbofan engines with engine assembly, P/N 2447M10G01 or P/N 2447M10G02, installed. The NPRM published in the Federal Register on May 10, 2016 (81 FR 28777). The NPRM was prompted by a report of a significant fan rub event. The NPRM proposed to require rework of the engine fan stator module assembly. We are issuing this AD to prevent failure of the fan blades and the load reduction device, loss of power to one or more engines, loss of thrust control, and loss of the airplane. ehiers on DSK5VPTVN1PROD with RULES Request To Add Terminating Action Japan Airlines and United Airlines requested that the airplane flight manual (AFM) limitations mandated by AD 2016–08–12, Amendment 39–18488 (81 FR 23581, April 22, 2016) (‘‘AD 2016–08–12’’), be removed from an aircraft that has complied with the fan case grind procedure mandated in this AD. They reason that once the fan case grind is completed on both engines installed on an airplane, there is no longer an unsafe condition. We agree. Once the fan case grind has been completed on both engines installed on an airplane, the unsafe condition no longer exists. With agreement from the Transport Airplane Directorate (TAD), we added a terminating action paragraph to this AD. Request To Add Compliance Methods Japan Airlines requested that alternate service documents be approved as compliance to AD 2016–06–08, Amendment 39–18439 (81 FR 14704, March 18, 2016) (‘‘AD 2016–06–08’’). They reason that the service documents provide the same procedure and the same post-rework configuration. We disagree. AD 2016–06–08 is a separate AD issued by the TAD, which VerDate Sep<11>2014 13:00 Oct 13, 2016 Jkt 241001 includes aircraft-level corrective actions. The commenter must contact the TAD to request a change to AD 2016–06–08. We did not change this AD. Request To Change Applicability GE requested that the applicability explicitly state that engine assembly, P/ N 2447M10G03, is not applicable to this AD. They reason that engine assembly, P/N 2447M10G03, is a new production part that does not contain the unsafe condition. We disagree. Since engine assembly, P/N 2447M10G03, is not listed in the applicability of this AD, it is not applicable to this AD. We did not change this AD. Request To Change Compliance Method GE requested that another procedure included within a new service bulletin, GE GEnx–1B Service Bulletin (SB) 72– 0317 R00, dated June 29, 2016, be added as a means of compliance to this AD. They reason that this new procedure achieves the same configuration as the proposed procedure. We agree. The new procedure in GE GEnx–1B SB 72–0317 R00, dated June 29, 2016, also corrects the unsafe condition addressed in this AD. We added GE GEnx–1B SB 72–0317 R00, dated June 29, 2016, as a means of compliance in this AD. Request To Change Compliance Time GE requested that we move the action specified in paragraph (f) Credit for Previous Action, to compliance paragraph (e) of this AD. They reason that this action is an equivalent method of performing the fan case rework. We agree. The action is equivalent to the current compliance, but located within a different service document. We revised paragraph (f) and paragraph (e) of this AD accordingly. Request To Change Affected ADs United Airlines requested that we list AD 2016–06–08 and AD 2016–08–12 in this AD. They reason that AD 2016–06– 08 and AD 2016–08–12 address the same unsafe condition as this AD and also mandate a fan case rework. We agree. AD 2016–06–08 and AD 2016–08–12 address the same unsafe condition as this AD. We list AD 2016– 06–08 and AD 2016–08–12 in paragraph (h) of this AD. Request To Change Affected ADs United Airlines requested that we supersede AD 2016–08–12 with this AD. They reason that AD 2016–06–08 and AD 2016–08–12 address the same unsafe condition of the engine and mandate a fan case rework procedure. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 We disagree. An AD that mandates engine-level corrective actions, ‘‘this AD’’, cannot supersede an AD, ‘‘AD 2016–08–12’’ that mandates aircraftlevel corrective actions. AD 2016–08–12 mandates aircraft limitations in addition to the engine rework procedure that can only be mandated at the aircraft level, not the engine level. We did not change this AD. Request To Change Operating Procedures United Airlines requested that we revise the operating procedures that require the ice removal procedure to be done every 5 minutes, rather than the preferred every 5 minutes or less, allowing the pilot to do the procedure prior to 5 minutes after Engine Indication and Crew Alerting System (EICAS) notification. United Airlines suggests the 5 minute requirement does not allow pilots to effectively manage the cockpit within reasonable parameters or room to operate. We disagree. The AFM operating procedures are mandated by aircraftlevel AD 2016–06–08 and AD 2016–08– 12, which were issued by the TAD. The commenter must contact the TAD to request a change to AD 2016–06–08 or AD 2016–08–12. We did not change this AD. Request To Change Compliance Time United Airlines requested that we allow installation of engine assembly, P/ N 2477M10G03, by using GE GEnx–1B SB 72–0317 to modify the engine instead of using the fan grind rework procedure as compliance to AD 2016– 08–12. They reason that the procedure in GE GEnx–1B SB 72–0317 achieves the same engine outcome as the currently mandated compliance. We disagree. AD 2016–08–12 was issued by the TAD. The commenter must contact the TAD to request a change to AD 2016–08–12. We did not change this AD. 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 for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic E:\FR\FM\14OCR1.SGM 14OCR1 Federal Register / Vol. 81, No. 199 / Friday, October 14, 2016 / Rules and Regulations burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed GE GEnx–1B SB 72– 0314 R00, dated April 1, 2016. The SB describes procedures for increasing the clearance of the fan stator module assembly. We also reviewed GE GEnx– 1B SB 72–0309 R00, dated March 11, 2016. That SB describes procedures for increasing the clearance of the fan stator module assembly. We also reviewed GE GEnx–1B SB 72–0317 R00, dated June 29, 2016. That SB releases a new fan stator module assembly. 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. Costs of Compliance We estimate that this AD affects 89 engines installed on airplanes of U.S. registry. We also estimate that it will take about 40 hours per engine to comply with 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 $302,600. 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. ehiers on DSK5VPTVN1PROD with RULES 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 13:00 Oct 13, 2016 Jkt 241001 70927 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. (i) Use paragraphs 3.B.(1) through 3.B.(6) or 3.C.(1) through 3.C.(6) of the Accomplishment Instructions of GE GEnx–1B Service Bulletin (SB) 72–0314 R00, dated April 1, 2016, to do the modification. (ii) Use paragraphs 3.B.(1) through 3.B.(6) or 3.C.(1) through 3.C.(6) of the Accomplishment Instructions of GE GEnx–1B SB 72–0309 R00, dated March 11, 2016, to do the modification. (iii) Use paragraph 3.A. of the Accomplishment Instructions of GE GEnx–1B SB 72–0317 R00, dated June 29, 2016, to do the modification. (2) Reserved. List of Subjects in 14 CFR Part 39 Compliance with this AD constitutes terminating action for AD 2016–06–08, Amendment 39–18439 (81 FR 14704, March 18, 2016) (‘‘AD 2016–06–08’’) and AD 2016– 08–12, Amendment 39–18488 (81 FR 23581, April 22, 2016) (‘‘AD 2016–08–12’’), provided that all of the airplanes within the operator’s fleet that have engines identified in paragraph (c) of this AD are modified as specified in paragraph (e) of this AD. After fleet incorporation of this AD, do not install any engine listed in paragraph (c) of this AD unless the engine is modified as specified in paragraph (e) of this AD, or AD 2016–06–08, or AD 2016–08–12. 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): ■ 2016–20–15 General Electric Company: Amendment 39–18681; Docket No. FAA–2016–5872; Directorate Identifier 2016–NE–11–AD. (a) Effective Date This AD is effective November 18, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all General Electric Company (GE) GEnx–1B64/P2, –1B67/P2, –1B70/P2, –1B70C/P2, –1B70/75/P2, and –1B74/75/P2 turbofan engines with engine assembly, part number (P/N) 2447M10G01 or P/N 2447M10G02, installed. (d) Unsafe Condition This AD was prompted by a report of a significant fan rub event. We are issuing this AD to prevent failure of the fan blades and the load reduction device, loss of power to one or more engines, loss of thrust control, and loss of the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Modify the fan stator module assembly, with one of the following methods, before December 31, 2016. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 (f) Terminating Action (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) AD 2016–06–08 and AD 2016–08–12 pertain to the subject of this AD. (i) 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) GEnx– 1B Service Bulletin (SB) 72–0309 R00, dated March 11, 2016. (ii) GE GEnx–1B SB 72–0314 R00, dated April 1, 2016. (iii) GE GEnx–1B SB 72–0317 R00, dated June 29, 2016. (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 & Propeller Directorate, 1200 District Avenue, Burlington, MA. For E:\FR\FM\14OCR1.SGM 14OCR1 70928 Federal Register / Vol. 81, No. 199 / Friday, October 14, 2016 / Rules and Regulations information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information 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 September 30, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–24795 Filed 10–13–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6551; Directorate Identifier 2013–SW–070–AD; Amendment 39–18682; AD 2016–21–01] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron (Bell) Model 430 helicopters. This AD requires establishing a life limit for a certain main rotor hub attachment bolt (bolt) and removing from service each bolt that has met or exceeded its life limit. This AD was prompted by a documentation error that omitted the life limit of a certain part-numbered bolt from the Airworthiness Limitations section of the maintenance manual. The actions of this AD are intended to establish a life limit for a certain partnumbered bolt to prevent failure of a bolt, failure of a main rotor hub, and subsequent loss of control of a helicopter. SUMMARY: This AD is effective November 18, 2016. ADDRESSES: For service information identified in this final rule, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http://www.bellcustomer.com/files/. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. ehiers on DSK5VPTVN1PROD with RULES DATES: VerDate Sep<11>2014 13:00 Oct 13, 2016 Jkt 241001 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–2016– 6551; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the Transport Canada AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion On May 10, 2016, at 81 FR 28766, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to certain serial-numbered Bell Model 430 helicopters with bolt part number (P/N) MS21250–08083 installed. The NPRM proposed to require, within 10 hours time-in-service (TIS), revising the Airworthiness Limitations section of the applicable maintenance manual or Instructions for Continued Airworthiness (ICA) by establishing a life limit of 5,000 hours TIS for each bolt P/N MS21250–08083, determining the number of hours TIS for each bolt and using the helicopter’s hours if the hours TIS of a bolt is unknown, and removing from service each bolt that has reached or exceeded its life limit. The proposed requirements were intended to establish a life limit for the bolt to prevent failure of a bolt, failure of a main rotor hub, and subsequent loss of control of a helicopter. Transport Canada, which is the aviation authority for Canada, has issued Canadian AD No. CF–2013–26, dated September 24, 2013, to correct an unsafe condition for certain serialnumbered Bell Model 430 helicopters. Transport Canada advises that bolt P/N MS21250–08083, which replaced bolt P/N 20–065–08083 in 2009, has a retirement life of 5,000 hours. However, the retirement life for the replacement bolt was inadvertently omitted from the limitations section of the Bell 430 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 maintenance manual. Transport Canada advises that this situation, if not corrected, could result in failure of a bolt and loss of control of the helicopter. Transport Canada AD No. CF–2013–26 requires reviewing the helicopter records to determine if bolt P/N MS21250–08083 is installed, creating a historical service record, and establishing an airworthiness life of 5,000 hours air time. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (81 FR 28766, May 10, 2016). FAA’s Determination These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, Transport Canada, its technical representative, has notified us of the unsafe condition described in its AD. We are issuing this AD because we evaluated all information provided by Transport Canada and determined the unsafe condition exists and is likely to exist or develop on other helicopters of the same type design and that air safety and the public interest require adopting the AD requirements as proposed. Differences Between This AD and the Transport Canada AD This AD requires compliance within 10 hours TIS, while the Transport Canada AD requires compliance within 60 days. Related Service Information We reviewed Bell Helicopter Alert Service Bulletin 430–12–47, dated November 14, 2012 (ASB). The ASB states that original bolt P/N 20–065– 08083 has a retirement life of 5,000 hours but has been replaced by standard bolt P/N MS21250–08083, which does not have a life limit listed in the maintenance manual. The purpose of the ASB is to establish a life limit of 5,000 hours for the replacement bolt. Bell specifies reviewing the aircraft records back to January 2009 to determine which part-numbered bolts are installed. If a replacement bolt P/N MS21250–08083 is installed, the ASB specifies using data from aircraft records to create a historical service record for the replacement bolts and reflecting the 5,000 hours life limit. The ASB also specifies updating the Bell 430 maintenance manual. E:\FR\FM\14OCR1.SGM 14OCR1

Agencies

[Federal Register Volume 81, Number 199 (Friday, October 14, 2016)]
[Rules and Regulations]
[Pages 70925-70928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24795]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5872; Directorate Identifier 2016-NE-11-AD; 
Amendment 39-18681; AD 2016-20-15]
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-1B64/P2, -1B67/P2, -1B70/P2, -1B70C/
P2, -1B70/75/P2, and -1B74/75/P2 turbofan engines with engine assembly, 
part number (P/N) 2447M10G01 or P/N 2447M10G02, installed. This AD was 
prompted by a report of a significant fan rub event. This AD requires 
rework of the engine fan stator module assembly. We are issuing this AD 
to prevent failure of the fan blades and the load reduction device, 
loss of power to one or more engines, loss of thrust control, and loss 
of the airplane.

DATES: This AD is effective November 18, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 18, 
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 referenced 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. It is also available on 
the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-5872.

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-2016-
5872; 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

[[Page 70926]]

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-1B64/P2, -1B67/
P2, -1B70/P2, -1B70C/P2, -1B70/75/P2, and -1B74/75/P2 turbofan engines 
with engine assembly, P/N 2447M10G01 or P/N 2447M10G02, installed. The 
NPRM published in the Federal Register on May 10, 2016 (81 FR 28777). 
The NPRM was prompted by a report of a significant fan rub event. The 
NPRM proposed to require rework of the engine fan stator module 
assembly. We are issuing this AD to prevent failure of the fan blades 
and the load reduction device, loss of power to one or more engines, 
loss of thrust control, and loss of the airplane.

Request To Add Terminating Action

    Japan Airlines and United Airlines requested that the airplane 
flight manual (AFM) limitations mandated by AD 2016-08-12, Amendment 
39-18488 (81 FR 23581, April 22, 2016) (``AD 2016-08-12''), be removed 
from an aircraft that has complied with the fan case grind procedure 
mandated in this AD. They reason that once the fan case grind is 
completed on both engines installed on an airplane, there is no longer 
an unsafe condition.
    We agree. Once the fan case grind has been completed on both 
engines installed on an airplane, the unsafe condition no longer 
exists. With agreement from the Transport Airplane Directorate (TAD), 
we added a terminating action paragraph to this AD.

Request To Add Compliance Methods

    Japan Airlines requested that alternate service documents be 
approved as compliance to AD 2016-06-08, Amendment 39-18439 (81 FR 
14704, March 18, 2016) (``AD 2016-06-08''). They reason that the 
service documents provide the same procedure and the same post-rework 
configuration.
    We disagree. AD 2016-06-08 is a separate AD issued by the TAD, 
which includes aircraft-level corrective actions. The commenter must 
contact the TAD to request a change to AD 2016-06-08. We did not change 
this AD.

Request To Change Applicability

    GE requested that the applicability explicitly state that engine 
assembly, P/N 2447M10G03, is not applicable to this AD. They reason 
that engine assembly, P/N 2447M10G03, is a new production part that 
does not contain the unsafe condition.
    We disagree. Since engine assembly, P/N 2447M10G03, is not listed 
in the applicability of this AD, it is not applicable to this AD. We 
did not change this AD.

Request To Change Compliance Method

    GE requested that another procedure included within a new service 
bulletin, GE GEnx-1B Service Bulletin (SB) 72-0317 R00, dated June 29, 
2016, be added as a means of compliance to this AD. They reason that 
this new procedure achieves the same configuration as the proposed 
procedure.
    We agree. The new procedure in GE GEnx-1B SB 72-0317 R00, dated 
June 29, 2016, also corrects the unsafe condition addressed in this AD. 
We added GE GEnx-1B SB 72-0317 R00, dated June 29, 2016, as a means of 
compliance in this AD.

Request To Change Compliance Time

    GE requested that we move the action specified in paragraph (f) 
Credit for Previous Action, to compliance paragraph (e) of this AD. 
They reason that this action is an equivalent method of performing the 
fan case rework.
    We agree. The action is equivalent to the current compliance, but 
located within a different service document. We revised paragraph (f) 
and paragraph (e) of this AD accordingly.

Request To Change Affected ADs

    United Airlines requested that we list AD 2016-06-08 and AD 2016-
08-12 in this AD. They reason that AD 2016-06-08 and AD 2016-08-12 
address the same unsafe condition as this AD and also mandate a fan 
case rework.
    We agree. AD 2016-06-08 and AD 2016-08-12 address the same unsafe 
condition as this AD. We list AD 2016-06-08 and AD 2016-08-12 in 
paragraph (h) of this AD.

Request To Change Affected ADs

    United Airlines requested that we supersede AD 2016-08-12 with this 
AD. They reason that AD 2016-06-08 and AD 2016-08-12 address the same 
unsafe condition of the engine and mandate a fan case rework procedure.
    We disagree. An AD that mandates engine-level corrective actions, 
``this AD'', cannot supersede an AD, ``AD 2016-08-12'' that mandates 
aircraft-level corrective actions. AD 2016-08-12 mandates aircraft 
limitations in addition to the engine rework procedure that can only be 
mandated at the aircraft level, not the engine level. We did not change 
this AD.

Request To Change Operating Procedures

    United Airlines requested that we revise the operating procedures 
that require the ice removal procedure to be done every 5 minutes, 
rather than the preferred every 5 minutes or less, allowing the pilot 
to do the procedure prior to 5 minutes after Engine Indication and Crew 
Alerting System (EICAS) notification. United Airlines suggests the 5 
minute requirement does not allow pilots to effectively manage the 
cockpit within reasonable parameters or room to operate.
    We disagree. The AFM operating procedures are mandated by aircraft-
level AD 2016-06-08 and AD 2016-08-12, which were issued by the TAD. 
The commenter must contact the TAD to request a change to AD 2016-06-08 
or AD 2016-08-12. We did not change this AD.

Request To Change Compliance Time

    United Airlines requested that we allow installation of engine 
assembly, P/N 2477M10G03, by using GE GEnx-1B SB 72-0317 to modify the 
engine instead of using the fan grind rework procedure as compliance to 
AD 2016-08-12. They reason that the procedure in GE GEnx-1B SB 72-0317 
achieves the same engine outcome as the currently mandated compliance.
    We disagree. AD 2016-08-12 was issued by the TAD. The commenter 
must contact the TAD to request a change to AD 2016-08-12. We did not 
change this AD.

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 for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic

[[Page 70927]]

burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed GE GEnx-1B SB 72-0314 R00, dated April 1, 2016. The SB 
describes procedures for increasing the clearance of the fan stator 
module assembly. We also reviewed GE GEnx-1B SB 72-0309 R00, dated 
March 11, 2016. That SB describes procedures for increasing the 
clearance of the fan stator module assembly. We also reviewed GE GEnx-
1B SB 72-0317 R00, dated June 29, 2016. That SB releases a new fan 
stator module assembly. 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.

Costs of Compliance

    We estimate that this AD affects 89 engines installed on airplanes 
of U.S. registry. We also estimate that it will take about 40 hours per 
engine to comply with 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 $302,600.

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):

2016-20-15 General Electric Company: Amendment 39-18681; Docket No. 
FAA-2016-5872; Directorate Identifier 2016-NE-11-AD.

(a) Effective Date

    This AD is effective November 18, 2016.

 (b) Affected ADs

    None.

(c) Applicability

    This AD applies to all General Electric Company (GE) GEnx-1B64/
P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/75/P2, and -1B74/75/P2 
turbofan engines with engine assembly, part number (P/N) 2447M10G01 
or P/N 2447M10G02, installed.

(d) Unsafe Condition

    This AD was prompted by a report of a significant fan rub event. 
We are issuing this AD to prevent failure of the fan blades and the 
load reduction device, loss of power to one or more engines, loss of 
thrust control, and loss of the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Modify the fan stator module assembly, with one of the 
following methods, before December 31, 2016.
    (i) Use paragraphs 3.B.(1) through 3.B.(6) or 3.C.(1) through 
3.C.(6) of the Accomplishment Instructions of GE GEnx-1B Service 
Bulletin (SB) 72-0314 R00, dated April 1, 2016, to do the 
modification.
    (ii) Use paragraphs 3.B.(1) through 3.B.(6) or 3.C.(1) through 
3.C.(6) of the Accomplishment Instructions of GE GEnx-1B SB 72-0309 
R00, dated March 11, 2016, to do the modification.
    (iii) Use paragraph 3.A. of the Accomplishment Instructions of 
GE GEnx-1B SB 72-0317 R00, dated June 29, 2016, to do the 
modification.
    (2) Reserved.

(f) Terminating Action

    Compliance with this AD constitutes terminating action for AD 
2016-06-08, Amendment 39-18439 (81 FR 14704, March 18, 2016) (``AD 
2016-06-08'') and AD 2016-08-12, Amendment 39-18488 (81 FR 23581, 
April 22, 2016) (``AD 2016-08-12''), provided that all of the 
airplanes within the operator's fleet that have engines identified 
in paragraph (c) of this AD are modified as specified in paragraph 
(e) of this AD. After fleet incorporation of this AD, do not install 
any engine listed in paragraph (c) of this AD unless the engine is 
modified as specified in paragraph (e) of this AD, or AD 2016-06-08, 
or AD 2016-08-12.

(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) AD 2016-06-08 and AD 2016-08-12 pertain to the subject of 
this AD.

(i) 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) GEnx-1B Service Bulletin (SB) 
72-0309 R00, dated March 11, 2016.
    (ii) GE GEnx-1B SB 72-0314 R00, dated April 1, 2016.
    (iii) GE GEnx-1B SB 72-0317 R00, dated June 29, 2016.
    (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 & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For

[[Page 70928]]

information on the availability of this material at the FAA, call 
781-238-7125.
    (5) You may view this service information 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 September 30, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-24795 Filed 10-13-16; 8:45 am]
BILLING CODE 4910-13-P