81 FR 70925 - Airworthiness Directives; General Electric Company Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 199 (October 14, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 199 (October 14, 2016)
| Page Range | 70925-70928 | |
| FR Document | 2016-24795 |
[Federal Register Volume 81, Number 199 (Friday, October 14, 2016)] [Rules and Regulations] [Pages 70925-70928] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-24795] ======================================================================= ----------------------------------------------------------------------- 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: [email protected]. 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: [email protected]. 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: [email protected]. (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: [email protected]. (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: [email protected]. (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
![Federal Register / Vol. 81, No. 199 / Friday, October 14, 2016 / Rules and Regulations 70925
Qinfiltration_83 = Qs_83 + Q 83 Opportunity Commission’s DEPARTMENT OF TRANSPORTATION
Where: recommendation to indicate that FCA
begins prompt, thorough, and impartial Federal Aviation Administration
Qinfiltration_95 and Qinfiltration_83 = total
infiltration air heat in cooling mode, investigations within 10 days of
calculated at the 95 °F and 83 °F dry- receiving notice of harassment 14 CFR Part 39
bulb outdoor conditions in Table 1 of allegations. [Docket No. FAA–2016–5872; Directorate
this appendix, in Btu/h. Identifier 2016–NE–11–AD; Amendment 39–
Qs_95 and Qs_83 = sensible heat added to the The FCA will continue to publish
18681; AD 2016–20–15]
room by infiltration air, calculated at the new or revised policy statements in
95 °F and 83 °F dry-bulb outdoor their full text. RIN 2120–AA64
conditions in Table 1 of this appendix,
in Btu/h. FCA Board Policy Statements Airworthiness Directives; General
Ql_95 and Ql_83 = latent heat added to the Electric Company Turbofan Engines
room by infiltration air, calculated at the FCA–PS–34 Disclosure of the Issuance
95 °F and 83 °F dry-bulb outdoor and Termination of Enforcement AGENCY: Federal Aviation
conditions in Table 1 of this appendix, Documents Administration (FAA), DOT.
in Btu/h. FCA–PS–37 Communications During ACTION: Final rule.
* * * * * Rulemaking
SUMMARY: We are adopting a new
[FR Doc. 2016–24869 Filed 10–13–16; 8:45 am] FCA–PS–41 Alternative Means of airworthiness directive (AD) for all
BILLING CODE 6450–01–P Dispute Resolution General Electric Company (GE) GEnx–
FCA–PS–44 Travel 1B64/P2, –1B67/P2, –1B70/P2, –1B70C/
FCA–PS–53 Examination Philosophy P2, –1B70/75/P2, and –1B74/75/P2
FARM CREDIT ADMINISTRATION turbofan engines with engine assembly,
FCA–PS–59 Regulatory Philosophy part number (P/N) 2447M10G01 or P/N
12 CFR Chapter VI 2447M10G02, installed. This AD was
FCA–PS–62 Equal Employment
Farm Credit Administration Board Opportunity and Diversity prompted by a report of a significant fan
Policy Statements FCA–PS–64 Rules for the Transaction rub event. This AD requires rework of
the engine fan stator module assembly.
of Business of the Farm Credit
AGENCY: Farm Credit Administration. We are issuing this AD to prevent
Administration Board
ACTION: Notice of policy statements and failure of the fan blades and the load
index. FCA–PS–65 Release of Consolidated reduction device, loss of power to one
Reporting System Information or more engines, loss of thrust control,
SUMMARY: The Farm Credit FCA–PS–67 Nondiscrimination on the and loss of the airplane.
Administration (FCA), as part of its Basis of Disability in Agency DATES: This AD is effective November
annual public notification process, is 18, 2016.
Programs and Activities
publishing for notice an index of the 18 The Director of the Federal Register
Board policy statements currently in FCA–PS–68 FCS Building Association
Management Operations Policies approved the incorporation by reference
existence. Most of the policy statements of certain publications listed in this AD
remain unchanged since our last and Practices
as of November 18, 2016.
Federal Register notice on November 2, FCA–PS–71 Disaster Relief Efforts by ADDRESSES: For service information
2015, except for one as discussed below Farm Credit Institutions
on Equal Employment Opportunity and identified in this final rule, contact
FCA–PS–72 Financial Institution General Electric Company, GE Aviation,
Diversity.
Rating System (FIRS) Room 285, 1 Neumann Way, Cincinnati,
DATES: October 14, 2016.
FCA–PS–77 Borrower Privacy OH 45215; phone: 513–552–3272; email:
FOR FURTHER INFORMATION CONTACT: aviation.fleetsupport@ge.com. You may
Dale L. Aultman, Secretary to Board, FCA–PS–78 Official Names of Farm view this referenced service information
Farm Credit Administration, 1501 Credit Institutions at the FAA, Engine & Propeller
Farm Credit Drive, McLean, Virginia FCA–PS–79 Consideration and Directorate, 1200 District Avenue,
22102–5090, (703) 883–4009, TTY Referral of Supervisory Strategies Burlington, MA 01803. For information
(703) 883–4056; or and Enforcement Actions on the availability of this material at the
Mary Alice Donner, Senior Counsel, FAA, call 781–238–7125. It is also
Office of General Counsel, Farm FCA–PS–80 Cooperative Operating
available on the internet at http://
Credit Administration, 1501 Farm Philosophy—Serving the Members
www.regulations.gov by searching for
Credit Drive, McLean, Virginia of Farm Credit System Institutions
and locating Docket No. FAA–2016–
22102–5090, (703) 883–4020, TTY FCA–PS–81 Ethics, Independence, 5872.
(703) 883–4020. Arm’s-Length Role, Ex Parte
SUPPLEMENTARY INFORMATION: A list of Communications and Open Examining the AD Docket
the 18 FCA Board policy statements is Government You may examine the AD docket on
set forth below. FCA Board policy Dated: October 6, 2016.
the Internet at http://
statements may be viewed online at www.regulations.gov by searching for
Dale L. Aultman,
www.fca.gov/handbook.nsf. and locating Docket No. FAA–2016–
On August 8, 2016, the FCA Board Secretary, Farm Credit Administration Board. 5872; or in person at the Docket
ehiers on DSK5VPTVN1PROD with RULES
updated FCA–PS–62 on, ‘‘Equal [FR Doc. 2016–24680 Filed 10–13–16; 8:45 am] Management Facility between 9 a.m.
Employment Opportunity and BILLING CODE 6705–01–P and 5 p.m., Monday through Friday,
Diversity.’’ The policy was published in except Federal holidays. The AD docket
the Federal Register on August 12, 2016 contains this AD, the regulatory
(81 FR 53482). The policy was slightly evaluation, any comments received, and
edited at the Equal Employment other information. The address for the
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burden on any operator or increase the For the reasons discussed above, I (i) Use paragraphs 3.B.(1) through 3.B.(6) or
scope of this AD. certify that this AD: 3.C.(1) through 3.C.(6) of the
(1) Is not a ‘‘significant regulatory Accomplishment Instructions of GE GEnx–1B
Related Service Information Under 1 Service Bulletin (SB) 72–0314 R00, dated
action’’ under Executive Order 12866,
CFR Part 51 April 1, 2016, to do the modification.
(2) Is not a ‘‘significant rule’’ under
(ii) Use paragraphs 3.B.(1) through 3.B.(6)
We reviewed GE GEnx–1B SB 72– DOT Regulatory Policies and Procedures or 3.C.(1) through 3.C.(6) of the
0314 R00, dated April 1, 2016. The SB (44 FR 11034, February 26, 1979), Accomplishment Instructions of GE GEnx–1B
describes procedures for increasing the (3) Will not affect intrastate aviation SB 72–0309 R00, dated March 11, 2016, to do
clearance of the fan stator module in Alaska to the extent that it justifies the modification.
assembly. We also reviewed GE GEnx– making a regulatory distinction, and (iii) Use paragraph 3.A. of the
1B SB 72–0309 R00, dated March 11, (4) Will not have a significant Accomplishment Instructions of GE GEnx–1B
2016. That SB describes procedures for economic impact, positive or negative, SB 72–0317 R00, dated June 29, 2016, to do
increasing the clearance of the fan stator on a substantial number of small entities the modification.
module assembly. We also reviewed GE under the criteria of the Regulatory (2) Reserved.
GEnx–1B SB 72–0317 R00, dated June Flexibility Act. (f) Terminating Action
29, 2016. That SB releases a new fan Compliance with this AD constitutes
List of Subjects in 14 CFR Part 39
stator module assembly. This service terminating action for AD 2016–06–08,
information is reasonably available Air transportation, Aircraft, Aviation Amendment 39–18439 (81 FR 14704, March
because the interested parties have safety, Incorporation by reference, 18, 2016) (‘‘AD 2016–06–08’’) and AD 2016–
access to it through their normal course Safety. 08–12, Amendment 39–18488 (81 FR 23581,
of business or by the means identified April 22, 2016) (‘‘AD 2016–08–12’’),
Adoption of the Amendment provided that all of the airplanes within the
in the ADDRESSES section.
Accordingly, under the authority operator’s fleet that have engines identified
Costs of Compliance delegated to me by the Administrator, in paragraph (c) of this AD are modified as
specified in paragraph (e) of this AD. After
We estimate that this AD affects 89 the FAA amends 14 CFR part 39 as
fleet incorporation of this AD, do not install
engines installed on airplanes of U.S. follows: any engine listed in paragraph (c) of this AD
registry. We also estimate that it will unless the engine is modified as specified in
take about 40 hours per engine to PART 39—AIRWORTHINESS paragraph (e) of this AD, or AD 2016–06–08,
comply with this AD. The average labor DIRECTIVES or AD 2016–08–12.
rate is $85 per hour. Based on these ■ 1. The authority citation for part 39 (g) Alternative Methods of Compliance
figures, we estimate the total cost of this continues to read as follows: (AMOCs)
AD to U.S. operators to be $302,600. The Manager, Engine Certification Office,
Authority: 49 U.S.C. 106(g), 40113, 44701.
Authority for This Rulemaking FAA, may approve AMOCs to this AD. Use
§ 39.13 [Amended] the procedures found in 14 CFR 39.19 to
Title 49 of the United States Code make your request. You may email your
specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by adding request to: ANE-AD-AMOC@faa.gov.
rules on aviation safety. Subtitle I, the following new airworthiness
directive (AD): (h) Related Information
section 106, describes the authority of
(1) For more information about this AD,
the FAA Administrator. Subtitle VII: 2016–20–15 General Electric Company:
contact Christopher McGuire, Aerospace
Aviation Programs, describes in more Amendment 39–18681; Docket No.
Engineer, Engine Certification Office, FAA,
detail the scope of the Agency’s FAA–2016–5872; Directorate Identifier
Engine & Propeller Directorate, 1200 District
authority. 2016–NE–11–AD.
Avenue, Burlington, MA 01803; phone: 781–
We are issuing this rulemaking under (a) Effective Date 238–7120; fax: 781–238–7199; email:
the authority described in Subtitle VII, This AD is effective November 18, 2016. chris.mcguire@faa.gov.
Part A, Subpart III, Section 44701: (2) AD 2016–06–08 and AD 2016–08–12
(b) Affected ADs pertain to the subject of this AD.
‘‘General requirements.’’ Under that
section, Congress charges the FAA with None. (i) Material Incorporated by Reference
promoting safe flight of civil aircraft in (c) Applicability (1) The Director of the Federal Register
air commerce by prescribing regulations This AD applies to all General Electric approved the incorporation by reference
for practices, methods, and procedures Company (GE) GEnx–1B64/P2, –1B67/P2, (IBR) of the service information listed in this
the Administrator finds necessary for –1B70/P2, –1B70C/P2, –1B70/75/P2, and paragraph under 5 U.S.C. 552(a) and 1 CFR
safety in air commerce. This regulation –1B74/75/P2 turbofan engines with engine part 51.
is within the scope of that authority assembly, part number (P/N) 2447M10G01 or (2) You must use this service information
because it addresses an unsafe condition P/N 2447M10G02, installed. as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
that is likely to exist or develop on (d) Unsafe Condition (i) General Electric Company (GE) GEnx–
products identified in this rulemaking This AD was prompted by a report of a 1B Service Bulletin (SB) 72–0309 R00, dated
action. significant fan rub event. We are issuing this March 11, 2016.
Regulatory Findings AD to prevent failure of the fan blades and (ii) GE GEnx–1B SB 72–0314 R00, dated
the load reduction device, loss of power to April 1, 2016.
This AD will not have federalism one or more engines, loss of thrust control, (iii) GE GEnx–1B SB 72–0317 R00, dated
implications under Executive Order and loss of the airplane. June 29, 2016.
13132. This AD will not have a (3) For GE service information identified in
(e) Compliance
ehiers on DSK5VPTVN1PROD with RULES
this AD, contact General Electric Company,
substantial direct effect on the States, on
Comply with this AD within the GE Aviation, Room 285, 1 Neumann Way,
the relationship between the national compliance times specified, unless already Cincinnati, OH 45215; phone: 513–552–3272;
government and the States, or on the done. email: aviation.fleetsupport@ge.com.
distribution of power and (1) Modify the fan stator module assembly, (4) You may view this service information
responsibilities among the various with one of the following methods, before at FAA, Engine & Propeller Directorate, 1200
levels of government. December 31, 2016. District Avenue, Burlington, MA. For
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information on the availability of this Examining the AD Docket maintenance manual. Transport Canada
material at the FAA, call 781–238–7125. advises that this situation, if not
(5) You may view this service information You may examine the AD docket on
the Internet at http:// corrected, could result in failure of a
at the National Archives and Records
Administration (NARA). For information on www.regulations.gov by searching for bolt and loss of control of the helicopter.
the availability of this material at NARA, call and locating Docket No. FAA–2016– Transport Canada AD No. CF–2013–26
202–741–6030, or go to: http:// 6551; or in person at the Docket requires reviewing the helicopter
www.archives.gov/federal-register/cfr/ibr- Operations Office between 9 a.m. and 5 records to determine if bolt P/N
locations.html. p.m., Monday through Friday, except MS21250–08083 is installed, creating a
Issued in Burlington, Massachusetts, on Federal holidays. The AD docket historical service record, and
September 30, 2016. contains this AD, the Transport Canada establishing an airworthiness life of
Colleen M. D’Alessandro, AD, the economic evaluation, any 5,000 hours air time.
Manager, Engine & Propeller Directorate, comments received, and other
information. The street address for the Comments
Aircraft Certification Service.
[FR Doc. 2016–24795 Filed 10–13–16; 8:45 am] Docket Operations Office (phone: 800– We gave the public the opportunity to
BILLING CODE 4910–13–P
647–5527) is U.S. Department of participate in developing this AD, but
Transportation, Docket Operations we did not receive any comments on the
Office, M–30, West Building Ground NPRM (81 FR 28766, May 10, 2016).
DEPARTMENT OF TRANSPORTATION Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590. FAA’s Determination
Federal Aviation Administration FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer, These helicopters have been approved
14 CFR Part 39 Safety Management Group, Rotorcraft by the aviation authority of Canada and
Directorate, FAA, 10101 Hillwood are approved for operation in the United
[Docket No. FAA–2016–6551; Directorate Pkwy, Fort Worth, TX 76177; telephone States. Pursuant to our bilateral
Identifier 2013–SW–070–AD; Amendment agreement with Canada, Transport
39–18682; AD 2016–21–01]
(817) 222–5110; email matthew.fuller@
faa.gov. Canada, its technical representative, has
RIN 2120–AA64 notified us of the unsafe condition
SUPPLEMENTARY INFORMATION:
described in its AD. We are issuing this
Airworthiness Directives; Bell Discussion AD because we evaluated all
Helicopter Textron Helicopters On May 10, 2016, at 81 FR 28766, the information provided by Transport
Federal Register published our notice of Canada and determined the unsafe
AGENCY: Federal Aviation condition exists and is likely to exist or
Administration (FAA), DOT. proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by develop on other helicopters of the same
ACTION: Final rule. type design and that air safety and the
adding an AD that would apply to
certain serial-numbered Bell Model 430 public interest require adopting the AD
SUMMARY: We are adopting a new
helicopters with bolt part number (P/N) requirements as proposed.
airworthiness directive (AD) for certain
Bell Helicopter Textron (Bell) Model MS21250–08083 installed. The NPRM Differences Between This AD and the
430 helicopters. This AD requires proposed to require, within 10 hours
Transport Canada AD
establishing a life limit for a certain time-in-service (TIS), revising the
main rotor hub attachment bolt (bolt) Airworthiness Limitations section of the This AD requires compliance within
and removing from service each bolt applicable maintenance manual or 10 hours TIS, while the Transport
that has met or exceeded its life limit. Instructions for Continued Canada AD requires compliance within
This AD was prompted by a Airworthiness (ICA) by establishing a 60 days.
documentation error that omitted the life limit of 5,000 hours TIS for each
bolt P/N MS21250–08083, determining Related Service Information
life limit of a certain part-numbered bolt
from the Airworthiness Limitations the number of hours TIS for each bolt
We reviewed Bell Helicopter Alert
section of the maintenance manual. The and using the helicopter’s hours if the
hours TIS of a bolt is unknown, and Service Bulletin 430–12–47, dated
actions of this AD are intended to November 14, 2012 (ASB). The ASB
establish a life limit for a certain part- removing from service each bolt that has
reached or exceeded its life limit. The states that original bolt P/N 20–065–
numbered bolt to prevent failure of a 08083 has a retirement life of 5,000
bolt, failure of a main rotor hub, and proposed requirements were intended to
establish a life limit for the bolt to hours but has been replaced by standard
subsequent loss of control of a bolt P/N MS21250–08083, which does
helicopter. prevent failure of a bolt, failure of a
main rotor hub, and subsequent loss of not have a life limit listed in the
DATES: This AD is effective November control of a helicopter. maintenance manual. The purpose of
18, 2016. Transport Canada, which is the the ASB is to establish a life limit of
ADDRESSES: For service information aviation authority for Canada, has 5,000 hours for the replacement bolt.
identified in this final rule, contact Bell issued Canadian AD No. CF–2013–26, Bell specifies reviewing the aircraft
Helicopter Textron Canada Limited, dated September 24, 2013, to correct an records back to January 2009 to
12,800 Rue de l’Avenir, Mirabel, Quebec unsafe condition for certain serial- determine which part-numbered bolts
J7J1R4; telephone (450) 437–2862 or numbered Bell Model 430 helicopters. are installed. If a replacement bolt P/N
(800) 363–8023; fax (450) 433–0272; or Transport Canada advises that bolt P/N MS21250–08083 is installed, the ASB
ehiers on DSK5VPTVN1PROD with RULES
at http://www.bellcustomer.com/files/. MS21250–08083, which replaced bolt specifies using data from aircraft records
You may review the referenced service P/N 20–065–08083 in 2009, has a to create a historical service record for
information at the FAA, Office of the retirement life of 5,000 hours. However, the replacement bolts and reflecting the
Regional Counsel, Southwest Region, the retirement life for the replacement 5,000 hours life limit. The ASB also
10101 Hillwood Pkwy, Room 6N–321, bolt was inadvertently omitted from the specifies updating the Bell 430
Fort Worth, TX 76177. limitations section of the Bell 430 maintenance manual.
VerDate Sep<11>2014 13:00 Oct 13, 2016 Jkt 241001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\14OCR1.SGM 14OCR1](https://thefederalregister.org/doc/81_FR_71124/page/4.svg)
Document Created: 2016-10-14 00:01:27
Document Modified: 2016-10-14 00:01:27
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 18, 2016. | |
| 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: [email protected] | |
| FR Citation | 81 FR 70925 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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