82 FR 60106 - Airworthiness Directives; General Electric Company Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 242 (December 19, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 242 (December 19, 2017)
| Page Range | 60106-60108 | |
| FR Document | 2017-27248 |
[Federal Register Volume 82, Number 242 (Tuesday, December 19, 2017)] [Rules and Regulations] [Pages 60106-60108] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-27248] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0660; Product Identifier 2017-NE-21-AD; Amendment 39-19132; AD 2017-26-01] 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 certain General Electric Company (GE) GEnx-1B64/P2, -1B67/P2, -1B70/P2, -1B70/ 75/P2, -1B70C/P2, and -1B74/75/P2 turbofan engines. This AD was prompted by a report of the failure of the high-pressure turbine (HPT) stage 1 blade retainer and subsequent in-flight shutdown of the engine. This AD requires inspection of the HPT stage 1 blade retainer. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 23, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 23, 2018. 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; fax: 513-552-3329; email: [email protected]. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0660. 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-2017- 0660; 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 final rule, 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, ECO Branch, FAA, 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 certain GE GEnx-1B64/P2, - 1B67/P2, -1B70/P2, -1B70/75/P2, -1B70C/P2, and -1B74/75/P2 turbofan engines. The NPRM published in the Federal Register on September 1, 2017 (82 FR 41577). The NPRM was prompted by a report of the failure of the HPT stage 1 blade retainer and subsequent in-flight shutdown of the engine. The NPRM proposed to require inspection of the HPT stage 1 blade retainer. We are issuing this AD to correct the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Revise Compliance Time American Airlines (AA) requested that we change the compliance time in this AD to align with the compliance schedule in GE GEnx-1B Service Bulletin (SB) 72-0326 R02, revised August 16, 2017. AA indicated the SB identifies two populations of HPT stage 1 blade retainers, one that requires inspection at the next shop visit and a second that requires inspection when the part is removed from the engine. The proposed AD, however, proposed inspection of all affected retainers at next shop visit. Due to this discrepancy between the proposed AD and the SB, AA requested this AD require inspections of the HPT stage 1 blade retainers at next shop visit and at part removal, as required by GEnx- 1B SB 72-0326 R02. GE commented that, based on its analysis, conducting the required inspection of the HPT stage 1 blade retainer at its next piece-part exposure is sufficient. GE requested that this final rule AD be changed to require inspection of all affected parts at piece-part exposure rather than at the next shop visit. We partially agree. We disagree with AA that requiring inspections of HPT stage 1 blade retainers at next shop visit and at part removal, per GE GEnx-1B SB 72-0326 R02, revised August 16, 2017, is necessary. We agree with GE that the risk assessment justifies waiting until exposure of the part to perform the inspection and the change clarifies the compliance action. We revised the compliance section of this AD to require that the HPT stage 1 blade retainer be inspected at its next piece-part exposure. Request To Align Compliance by Part Population Japan Airlines (JAL) requested that the compliance be changed to two populations of parts with two different compliance intervals. JAL indicated this change would align this AD with the two populations of affected parts identified in GE GEnx-1B SB 72-0326 R02, revised August 16, 2017. We disagree. Although the SB specifies certain part numbers be inspected sooner than at piece-part exposure, our risk assessment determined that performing the inspection for all affected parts at piece-part exposure addresses the safety concern represented by failure of the HPT stage 1 blade retainer. We did not change this AD. Request To Incorporate Required for Compliance (RC) Label Into SB AA requested that we incorporate the RC label into GEnx-1B SB 72- 0326 R02, revised August 16, 2017. AA indicated this change would clarify which sections of the SB are required to accomplish this AD. Using the RC label in the SB would also be consistent with FAA Advisory Circular (AC) 20-176A, ``Service Bulletins Related to Airworthiness Directives and Indicating FAA Approval on Service Documents,'' dated June 16, 2014, and FAA Order 8110.117A, ``Service Bulletins Related to Airworthiness Directives,'' dated June 18, 2014. We disagree. FAA Order 8110.117A and AC 20-176A provide guidance, respectively, to FAA aviation safety engineers in the review of SBs and to design approval holders (DAHs) in the development and drafting of these SBs. These documents do not require use of the RC label by DAHs in drafting in SBs, and GE is not required to use this label. The paragraph from GE GEnx-1B SB 72-0326 R02, revised August 16, 2017, [[Page 60107]] that is incorporated by reference by this AD, clearly identifies the steps that operators must follow to perform the inspection. We did not change this AD. Request To Add Reference to Related SB An individual commenter requested that GE GEnx-1B SB 72-0327 R02, revised August 16, 2017, be mentioned in this AD since this SB is related to GEnx-1B SB 72-0326 R02, revised August 16, 2017. The commenter indicated GEnx-1B SB 72-0327 also relates to inspection of the stage one HPT blade retainer, but references an alternate part number. The commenter requested that the relationship between GEnx-1B SB 72-0327 R02 and GEnx-1B SB 72-0326 R02 be stated clearly. We partially agree. Although GE GEnx-1B SB 72-0327 R02, revised August 16, 2017, has a part number in common with the parts identified in GE GEnx-1B SB 72-0326 R02, revised August 16, 2017, the serial numbers for the parts identified in GEnx-1B SB 72-0327 differ from those in GEnx-1B SB 72-0326. The serial numbered parts identified in GEnx-1B SB 72-0327 pose a lower risk to flight safety and are not affected by this AD. We did not change this AD. Support for the AD The Air Line Pilots Association expressed support for the NPRM as written. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes:[Agr]re 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 burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 We reviewed GE GEnx-1B SB 72-0326 R02, revised August 16, 2017. The SB describes procedures for piece-part inspection of the HPT stage 1 blade retainer. 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 11 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspection of the HPT stage 1 blade 1 work-hour x $85 per $0 $85 $935 retainer. hour = $85. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2017-26-01 General Electric Company: Amendment 39-19132; Docket No. FAA-2017-0660; Product Identifier 2017-NE-21-AD. (a) Effective Date This AD is effective January 23, 2018. (b) Affected ADs None. [[Page 60108]] (c) Applicability This AD applies to General Electric Company (GE) GEnx-1B64/P2, - 1B67/P2, -1B70/P2, -1B70/75/P2, -1B70C/P2, and -1B74/75/P2 turbofan engines, with a high-pressure turbine (HPT) stage 1 blade retainer, part number (P/N) 2445M91P01 or 2383M99P02, with a serial number listed in Planning Information, Paragraph 1.A., of GE GEnx-1B Service Bulletin (SB) 72-0326 R02, revised August 16, 2017. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a report of the failure of the HPT stage 1 blade retainer and subsequent in-flight shutdown of the engine. We are issuing this AD to prevent failure of the HPT stage 1 blade retainer. The unsafe condition, if not corrected, could result in failure of one or more engines, loss of thrust control, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) At the next piece-part exposure of the HPT stage 1 blade retainer after the effective date of this AD, perform a one-time inspection of the HPT stage 1 blade retainer in accordance with the Accomplishment Instructions, paragraph 3.A.(1), in GE GEnx-1B SB 72- 0326 R02, revised August 16, 2017. (2) If any cracks are found in the HPT stage 1 blade retainer, or the retainer does not meet the dimensional criteria found in the Accomplishment Instructions, Paragraph 3.A.(1), in GEnx-1B SB 72- 0326 R02, revised August 16, 2017, replace the HPT stage 1 blade retainer with a part eligible for installation. (h) Definition For the purpose of this AD, ``piece-part exposure'' is defined as when the part is completely disassembled. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ECO Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD. You may email your request to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (j) Related Information For more information about this AD, contact Christopher McGuire, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: [email protected]. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) General Electric Company (GE) GEnx-1B Service Bulletin 72- 0326 R02, revised August 16, 2017. (ii) Reserved. (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; fax: 513-552-3329; email: [email protected]. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on December 11, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017-27248 Filed 12-18-17; 8:45 am] BILLING CODE 4910-13-P
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Administration Commissioned Officer contains this final rule, the regulatory is sufficient. GE requested that this final
Corps. evaluation, any comments received, and rule AD be changed to require
* * * * * other information. The address for the inspection of all affected parts at piece-
[FR Doc. 2017–27304 Filed 12–18–17; 8:45 am] Docket Office (phone: 800–647–5527) is part exposure rather than at the next
BILLING CODE 6760–01–P Document Management Facility, U.S. shop visit.
Department of Transportation, Docket We partially agree. We disagree with
Operations, M–30, West Building AA that requiring inspections of HPT
DEPARTMENT OF TRANSPORTATION Ground Floor, Room W12–140, 1200 stage 1 blade retainers at next shop visit
New Jersey Avenue SE, Washington, DC and at part removal, per GE GEnx–1B
Federal Aviation Administration 20590. SB 72–0326 R02, revised August 16,
FOR FURTHER INFORMATION CONTACT: 2017, is necessary. We agree with GE
14 CFR Part 39 Christopher McGuire, Aerospace that the risk assessment justifies waiting
Engineer, ECO Branch, FAA, 1200 until exposure of the part to perform the
[Docket No. FAA–2017–0660; Product inspection and the change clarifies the
Identifier 2017–NE–21–AD; Amendment 39–
District Avenue, Burlington, MA 01803;
phone: 781–238–7120; fax: 781–238– compliance action. We revised the
19132; AD 2017–26–01]
7199; email: chris.mcguire@faa.gov. compliance section of this AD to require
RIN 2120–AA64 SUPPLEMENTARY INFORMATION: that the HPT stage 1 blade retainer be
inspected at its next piece-part
Airworthiness Directives; General Discussion exposure.
Electric Company Turbofan Engines We issued a notice of proposed Request To Align Compliance by Part
AGENCY: Federal Aviation rulemaking (NPRM) to amend 14 CFR Population
Administration (FAA), DOT. part 39 by adding an AD that would
apply to certain GE GEnx–1B64/P2, Japan Airlines (JAL) requested that
ACTION: Final rule. the compliance be changed to two
–1B67/P2, –1B70/P2, –1B70/75/P2,
–1B70C/P2, and –1B74/75/P2 turbofan populations of parts with two different
SUMMARY: We are adopting a new
engines. The NPRM published in the compliance intervals. JAL indicated this
airworthiness directive (AD) for certain
Federal Register on September 1, 2017 change would align this AD with the
General Electric Company (GE) GEnx–
(82 FR 41577). The NPRM was two populations of affected parts
1B64/P2, –1B67/P2, –1B70/P2, –1B70/
prompted by a report of the failure of identified in GE GEnx–1B SB 72–0326
75/P2, –1B70C/P2, and –1B74/75/P2
the HPT stage 1 blade retainer and R02, revised August 16, 2017.
turbofan engines. This AD was
subsequent in-flight shutdown of the We disagree. Although the SB
prompted by a report of the failure of
engine. The NPRM proposed to require specifies certain part numbers be
the high-pressure turbine (HPT) stage 1
inspection of the HPT stage 1 blade inspected sooner than at piece-part
blade retainer and subsequent in-flight
retainer. We are issuing this AD to exposure, our risk assessment
shutdown of the engine. This AD
correct the unsafe condition on these determined that performing the
requires inspection of the HPT stage 1
products. inspection for all affected parts at piece-
blade retainer. We are issuing this AD
part exposure addresses the safety
to address the unsafe condition on these Comments concern represented by failure of the
products.
We gave the public the opportunity to HPT stage 1 blade retainer. We did not
DATES: This AD is effective January 23, participate in developing this final rule. change this AD.
2018. The following presents the comments
The Director of the Federal Register Request To Incorporate Required for
received on the NPRM and the FAA’s Compliance (RC) Label Into SB
approved the incorporation by reference response to each comment.
of a certain publication listed in this AD AA requested that we incorporate the
as of January 23, 2018. Request To Revise Compliance Time RC label into GEnx–1B SB 72–0326 R02,
ADDRESSES: For service information American Airlines (AA) requested revised August 16, 2017. AA indicated
identified in this final rule, contact that we change the compliance time in this change would clarify which
General Electric Company, GE-Aviation, this AD to align with the compliance sections of the SB are required to
Room 285, 1 Neumann Way, Cincinnati, schedule in GE GEnx–1B Service accomplish this AD. Using the RC label
OH 45215, phone: 513–552–3272; fax: Bulletin (SB) 72–0326 R02, revised in the SB would also be consistent with
513–552–3329; email: geae.aoc@ge.com. August 16, 2017. AA indicated the SB FAA Advisory Circular (AC) 20–176A,
You may view this service information identifies two populations of HPT stage ‘‘Service Bulletins Related to
at the FAA, Engine and Propeller 1 blade retainers, one that requires Airworthiness Directives and Indicating
Standards Branch, 1200 District inspection at the next shop visit and a FAA Approval on Service Documents,’’
Avenue, Burlington, MA. It is also second that requires inspection when dated June 16, 2014, and FAA Order
available on the internet at http:// the part is removed from the engine. 8110.117A, ‘‘Service Bulletins Related
www.regulations.gov by searching for The proposed AD, however, proposed to Airworthiness Directives,’’ dated June
and locating Docket No. FAA–2017– inspection of all affected retainers at 18, 2014.
0660. next shop visit. Due to this discrepancy We disagree. FAA Order 8110.117A
between the proposed AD and the SB, and AC 20–176A provide guidance,
Examining the AD Docket respectively, to FAA aviation safety
AA requested this AD require
You may examine the AD docket on inspections of the HPT stage 1 blade engineers in the review of SBs and to
sradovich on DSK3GMQ082PROD with RULES
the internet at http:// retainers at next shop visit and at part design approval holders (DAHs) in the
www.regulations.gov by searching for removal, as required by GEnx-1B SB 72– development and drafting of these SBs.
and locating Docket No. FAA–2017– 0326 R02. These documents do not require use of
0660; or in person at the Docket GE commented that, based on its the RC label by DAHs in drafting in SBs,
Management Facility between 9 a.m. analysis, conducting the required and GE is not required to use this label.
and 5 p.m., Monday through Friday, inspection of the HPT stage 1 blade The paragraph from GE GEnx–1B SB
except Federal holidays. The AD docket retainer at its next piece-part exposure 72–0326 R02, revised August 16, 2017,
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that is incorporated by reference by this 0327 differ from those in GEnx–1B SB We also determined that these
AD, clearly identifies the steps that 72–0326. The serial numbered parts changes will not increase the economic
operators must follow to perform the identified in GEnx–1B SB 72–0327 pose burden on any operator or increase the
inspection. We did not change this AD. a lower risk to flight safety and are not scope of this final rule.
affected by this AD. We did not change
Request To Add Reference to Related Related Service Information Under 1
SB this AD.
CFR Part 51
An individual commenter requested Support for the AD
that GE GEnx–1B SB 72–0327 R02, The Air Line Pilots Association We reviewed GE GEnx–1B SB 72–
revised August 16, 2017, be mentioned expressed support for the NPRM as 0326 R02, revised August 16, 2017. The
in this AD since this SB is related to written. SB describes procedures for piece-part
GEnx–1B SB 72–0326 R02, revised inspection of the HPT stage 1 blade
August 16, 2017. The commenter Conclusion retainer. This service information is
indicated GEnx–1B SB 72–0327 also We reviewed the relevant data, reasonably available because the
relates to inspection of the stage one considered the comments received, and interested parties have access to it
HPT blade retainer, but references an determined that air safety and the through their normal course of business
alternate part number. The commenter public interest require adopting this or by the means identified in the
requested that the relationship between final rule with the changes described ADDRESSES section.
GEnx–1B SB 72–0327 R02 and GEnx–1B previously and minor editorial changes.
SB 72–0326 R02 be stated clearly. We have determined that these minor Costs of Compliance
We partially agree. Although GE changes: We estimate that this AD affects 11
GEnx–1B SB 72–0327 R02, revised • Are consistent with the intent that
August 16, 2017, has a part number in engines installed on airplanes of U.S.
was proposed in the NPRM for
common with the parts identified in GE correcting the unsafe condition; and registry.
GEnx–1B SB 72–0326 R02, revised • Do not add any additional burden We estimate the following costs to
August 16, 2017, the serial numbers for upon the public than was already comply with this AD:
the parts identified in GEnx–1B SB 72– proposed in the NPRM.
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection of the HPT stage 1 blade retainer 1 work-hour × $85 per hour = $85 ................. $0 $85 $935
Authority for This Rulemaking delegated the authority to issue ADs List of Subjects in 14 CFR Part 39
Title 49 of the United States Code applicable to engines, propellers, and
associated appliances to the Manager, Air transportation, Aircraft, Aviation
specifies the FAA’s authority to issue safety, Incorporation by reference,
rules on aviation safety. Subtitle I, Engine and Propeller Standards Branch,
Policy and Innovation Division. Safety.
section 106, describes the authority of
the FAA Administrator. Subtitle VII: Adoption of the Amendment
Regulatory Findings
Aviation Programs, describes in more
detail the scope of the Agency’s Accordingly, under the authority
This AD will not have federalism
authority. delegated to me by the Administrator,
implications under Executive Order
We are issuing this rulemaking under the FAA amends 14 CFR part 39 as
13132. This AD will not have a follows:
the authority described in Subtitle VII, substantial direct effect on the States, on
Part A, Subpart III, Section 44701: the relationship between the national
‘‘General requirements.’’ Under that PART 39—AIRWORTHINESS
government and the States, or on the DIRECTIVES
section, Congress charges the FAA with
distribution of power and
promoting safe flight of civil aircraft in
responsibilities among the various ■ 1. The authority citation for part 39
air commerce by prescribing regulations
for practices, methods, and procedures levels of government. continues to read as follows:
the Administrator finds necessary for For the reasons discussed above, I Authority: 49 U.S.C. 106(g), 40113, 44701.
safety in air commerce. This regulation certify that this AD:
is within the scope of that authority § 39.13 [Amended]
(1) Is not a ‘‘significant regulatory
because it addresses an unsafe condition action’’ under Executive Order 12866, ■ 2. The FAA amends § 39.13 by adding
that is likely to exist or develop on the following new airworthiness
products identified in this rulemaking (2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures directive (AD):
action.
This AD is issued in accordance with (44 FR 11034, February 26, 1979), 2017–26–01 General Electric Company:
authority delegated by the Executive (3) Will not affect intrastate aviation Amendment 39–19132; Docket No.
sradovich on DSK3GMQ082PROD with RULES
Director, Aircraft Certification Service, FAA–2017–0660; Product Identifier
in Alaska, and
as authorized by FAA Order 8000.51C. 2017–NE–21–AD.
(4) Will not have a significant
In accordance with that order, issuance (a) Effective Date
economic impact, positive or negative,
of ADs is normally a function of the This AD is effective January 23, 2018.
on a substantial number of small entities
Compliance and Airworthiness
Division, but during this transition under the criteria of the Regulatory (b) Affected ADs
period, the Executive Director has Flexibility Act. None.
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(c) Applicability 238–7120; fax: 781–238–7199; email: instrument flight rules (IFR) operations
This AD applies to General Electric christopher.mcguire@faa.gov. at the airport. Additionally, the
Company (GE) GEnx–1B64/P2, –1B67/P2, (k) Material Incorporated by Reference geographic coordinates of the airport are
–1B70/P2, –1B70/75/P2, –1B70C/P2, and adjusted to coincide with the FAA’s
–1B74/75/P2 turbofan engines, with a high- (1) The Director of the Federal Register
approved the incorporation by reference aeronautical database.
pressure turbine (HPT) stage 1 blade retainer,
part number (P/N) 2445M91P01 or (IBR) of the service information listed in this DATES: Effective 0901 UTC, March 29,
2383M99P02, with a serial number listed in paragraph under 5 U.S.C. 552(a) and 1 CFR 2018. The Director of the Federal
Planning Information, Paragraph 1.A., of GE part 51. Register approves this incorporation by
GEnx–1B Service Bulletin (SB) 72–0326 R02, (2) You must use this service information
reference action under Title 1, Code of
revised August 16, 2017. as applicable to do the actions required by
this AD, unless the AD specifies otherwise. Federal Regulations, part 51, subject to
(d) Subject (i) General Electric Company (GE) GEnx– the annual revision of FAA Order
Joint Aircraft System Component (JASC) 1B Service Bulletin 72–0326 R02, revised 7400.11 and publication of conforming
Code 7250, Turbine Section. August 16, 2017. amendments.
(ii) Reserved. ADDRESSES: FAA Order 7400.11B,
(e) Unsafe Condition (3) For GE service information identified in
Airspace Designations and Reporting
This AD was prompted by a report of the this AD, contact General Electric Company,
failure of the HPT stage 1 blade retainer and GE-Aviation, Room 285, 1 Neumann Way, Points, and subsequent amendments can
subsequent in-flight shutdown of the engine. Cincinnati, OH 45215, phone: 513–552–3272; be viewed online at http://www.faa.gov/
We are issuing this AD to prevent failure of fax: 513–552–3329; email: geae.aoc@ge.com. air_traffic/publications/. For further
the HPT stage 1 blade retainer. The unsafe (4) You may view this service information information, you can contact the
condition, if not corrected, could result in at FAA, Engine and Propeller Standards Airspace Policy Group, Federal Aviation
failure of one or more engines, loss of thrust Branch, 1200 District Avenue, Burlington, Administration, 800 Independence
control, and damage to the airplane. MA. For information on the availability of Avenue SW, Washington, DC 20591;
this material at the FAA, call 781–238–7125. telephone: (202) 267–8783. The Order is
(f) Compliance
(5) You may view this service information
Comply with this AD within the also available for inspection at the
that is incorporated by reference at the
compliance times specified, unless already National Archives and Records National Archives and Records
done. Administration (NARA). For information on Administration (NARA). For
the availability of this material at NARA, call information on the availability of FAA
(g) Required Actions
202–741–6030, or go to: http:// Order 7400.11B at NARA, call (202)
(1) At the next piece-part exposure of the www.archives.gov/federal-register/cfr/ibr- 741–6030, or go to https://
HPT stage 1 blade retainer after the effective locations.html. www.archives.gov/federal-register/cfr/
date of this AD, perform a one-time
inspection of the HPT stage 1 blade retainer Issued in Burlington, Massachusetts, on ibr-locations.html.
in accordance with the Accomplishment December 11, 2017. FAA Order 7400.11, Airspace
Instructions, paragraph 3.A.(1), in GE GEnx– Robert J. Ganley, Designations and Reporting Points, is
1B SB 72–0326 R02, revised August 16, 2017. Manager, Engine and Propeller Standards published yearly and effective on
(2) If any cracks are found in the HPT stage Branch, Aircraft Certification Service. September 15.
1 blade retainer, or the retainer does not meet
the dimensional criteria found in the [FR Doc. 2017–27248 Filed 12–18–17; 8:45 am] FOR FURTHER INFORMATION CONTACT:
Accomplishment Instructions, Paragraph BILLING CODE 4910–13–P Jeffrey Claypool, Federal Aviation
3.A.(1), in GEnx–1B SB 72–0326 R02, revised Administration, Operations Support
August 16, 2017, replace the HPT stage 1 Group, Central Service Center, 10101
blade retainer with a part eligible for DEPARTMENT OF TRANSPORTATION Hillwood Parkway, Fort Worth, TX
installation. 76177; telephone (817) 222–5711.
Federal Aviation Administration
(h) Definition SUPPLEMENTARY INFORMATION:
For the purpose of this AD, ‘‘piece-part 14 CFR Part 71 Authority for This Rulemaking
exposure’’ is defined as when the part is
completely disassembled. [Docket No. FAA–2017–0459; Airspace The FAA’s authority to issue rules
Docket No. 17–AGL–14] regarding aviation safety is found in
(i) Alternative Methods of Compliance
(AMOCs) Title 49 of the United States Code.
Amendment of Class E Airspace; Subtitle I, Section 106 describes the
(1) The Manager, ECO Branch, FAA, has Greenwood/Wonder Lake, IL
the authority to approve AMOCs for this AD, authority of the FAA Administrator.
if requested using the procedures found in 14 AGENCY: Federal Aviation Subtitle VII, Aviation Programs,
CFR 39.19. In accordance with 14 CFR 39.19, Administration (FAA), DOT. describes in more detail the scope of the
send your request to your principal inspector ACTION: Final rule. agency’s authority. This rulemaking is
or local Flight Standards District Office, as promulgated under the authority
appropriate. If sending information directly SUMMARY: This action modifies Class E described in Subtitle VII, Part A,
to the manager of the ECO Branch, send it to airspace extending upward from 700 Subpart I, Section 40103. Under that
the attention of the person identified in
paragraph (j)(1) of this AD. You may email feet above the surface at Galt Field section, the FAA is charged with
your request to: ANE-AD-AMOC@faa.gov. Airport, Greenwood/Wonder Lake, IL. prescribing regulations to assign the use
(2) Before using any approved AMOC, This action is required due to the of airspace necessary to ensure the
notify your appropriate principal inspector, decommissioning of the Kenosha VHF safety of aircraft and the efficient use of
or lacking a principal inspector, the manager omnidirectional range (VOR), which airspace. This regulation is within the
sradovich on DSK3GMQ082PROD with RULES
of the local flight standards district office/ provided navigation guidance for the scope of that authority as it amends
certificate holding district office. standard instrument approach Class E airspace extending upward from
(j) Related Information procedures to this airport. The Kenosha 700 feet above the surface at Galt Field
For more information about this AD, VOR is being decommissioned as part of Airport, Greenwood/Wonder Lake, IL, to
contact Christopher McGuire, Aerospace the VOR Minimum Operational support standard instrument approach
Engineer, ECO Branch, FAA, 1200 District Network (MON) Program. This action procedures for IFR operations at the
Avenue, Burlington, MA 01803; phone: 781– enhances the safety and management of airport.
VerDate Sep<11>2014 16:00 Dec 18, 2017 Jkt 244001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\19DER1.SGM 19DER1](https://thefederalregister.org/doc/82_FR_60348/page/3.svg)
Document Created: 2017-12-19 01:31:04
Document Modified: 2017-12-19 01:31:04
| 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 January 23, 2018. | |
| Contact | Christopher McGuire, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 82 FR 60106 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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