[Federal Register Volume 82, Number 242 (Tuesday, December 19, 2017)]
[Rules and Regulations]
[Pages 60106-60108]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-27248]
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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.
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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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection of the HPT stage 1 blade 1 work-hour x $85 per $0 $85 $935
retainer. hour = $85.
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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]
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