[Federal Register Volume 84, Number 27 (Friday, February 8, 2019)]
[Rules and Regulations]
[Pages 2709-2713]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-01589]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0042; Product Identifier 2018-NE-25-AD; Amendment
39-19548; AD 2019-02-01]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2018-16-07,
which applied to certain General Electric Company (GE) GEnx turbofan
engines. AD 2018-16-07 required removal and replacement of affected
high-pressure turbine (HPT) stator cases (HPT cases). This AD retains
those requirements, but reduces certain compliance times. This AD was
prompted by the discovery of a quality escape at a manufacturing
facility and a determination that the compliance time for the removal
and replacement of certain HPT cases must be reduced. We are issuing
this AD to address the unsafe condition on these products.
DATES: This AD is effective February 25, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 25,
2019.
We must receive any comments on this AD by March 25, 2019.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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 service information at
the FAA, Engine and Propeller Standards Branch, 1200 District Avenue,
Burlington, MA. You may view this service information at the FAA,
Engine and Propeller Standards Branch, 1200 District Avenue,
Burlington, MA. For information on the availability of this material at
the FAA, call 781-238-7759. It is also available on the internet at
http://www.regulations.gov by searching for and locating Docket No.
FAA-2019-0042.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for
[[Page 2710]]
and locating Docket No. FAA-2019-0042; or in person at Docket
Operations 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 street address for Docket Operations (phone: 800-647-5527) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Herman Mak, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7147; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued AD 2018-16-07, Amendment 39-19347 (83 FR 36724, July 31,
2018) (``AD 2018-16-07''), for certain GE GEnx-1B54, -1B58, -1B64, -
1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B54/
P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P1, -1B70/72/P1, -
1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B70C/P2, -1B70/72/P2, -1B70/75/P2,
-1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/P2, -2B67, -2B67B,
and -2B67/P turbofan engines. AD 2018-16-07 required removal of
affected HPT cases from service and their replacement with a part
eligible for installation. AD 2018-16-07 was prompted by the discovery
of a quality escape at a manufacturing facility involving unapproved
reworks on HPT cases. We issued AD 2018-16-07 to address failure of the
HPT case, which could result in engine fire and damage to the airplane.
Actions Since AD 2018-16-07 was Issued
Since we issued AD 2018-16-07, we have received new data from the
manufacturer and have determined that certain HPT cases may have a
reduced fatigue life than previously determined. Because of this
reduced fatigue life, the HPT cases must be removed and replaced at
reduced compliance times. Failure to remove and replace the HPT cases
within the reduced compliance times could result in failure of the HPT
case resulting in the unsafe condition identified above.
Related Service Information Under 1 CFR Part 51
We reviewed GE Service Bulletin (SB) GEnx-2B S/B 72-0360, Revision
04, dated December 4, 2018, and GE SB GEnx-1B S/B 72-0424, Revision 04,
dated December 3, 2018. This service information describes procedures
for removing the affected HPT cases from the engine. GE SB GEnx-1B S/B
72-0424 is effective for GEnx-1B engines with the serial numbers of HPT
cases listed therein. GE SB GEnx-2B S/B 72-0360 is effective for GEnx-
2B engines with the serial numbers of HPT cases listed therein. 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.
Other Related Service Information
We reviewed Inspection 001, Subtask 72-52-01-230-001, of GEnx-1B
Cleaning, Inspection, and Repair Manual GEK112862, Rev 27, dated April
30, 2018, and GEnx-2B Cleaning, Inspection, and Repair Manual
GEK114120, Rev 20, dated April 30, 2018. These manuals provide guidance
for conducting Class A fluorescent penetrant inspections.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires removal of the affected HPT cases from service and
their replacement with a part eligible for installation.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule
because of a quality escape at a manufacturing facility involving
unapproved rework on HPT cases, which could result in failure of the
HPT case and subsequent engine fire and damage to the airplane.
Additionally, the compliance time for the required action is shorter
than the time necessary for the public to comment and for publication
of the final rule. Therefore, we find good cause that notice and
opportunity for prior public comment are impracticable. In addition,
for the reasons stated above, we find that good cause exists for making
this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this final rule. Send your comments to an address
listed under the ADDRESSES section. Include the docket number FAA-2019-
0042 and Product Identifier 2018-NE-25-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this final rule. We will
consider all comments received by the closing date and may amend this
final rule because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this final rule.
Costs of Compliance
We estimate that this AD affects 7 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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Removal and replacement of HPT cases 0 work-hours x $85 per $362,400 $362,400 $2,536,800
hour = $0.
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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.
[[Page 2711]]
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
We have determined that 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 removing Airworthiness Directive (AD)
2018-16-07, Amendment 39-19347 (83 FR 36724, July 31, 2018), and adding
the following new AD:
2019-02-01 General Electric Company: Amendment 39-19548; Docket No.
FAA-2019-0042; Product Identifier 2018-NE-25-AD.
(a) Effective Date
This AD is effective February 25, 2019.
(b) Affected ADs
This AD replaces AD 2018-16-07, Amendment 39-19347 (83 FR 36724,
July 31, 2018) (``AD 2018-16-07'').
(c) Applicability
This AD applies to General Electric Company (GE) GEnx-1B54, -
1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -
1B70/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/
P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B70C/P2, -
1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2,
-1B78/P2, -2B67, -2B67B, and -2B67/P turbofan engines with a high-
pressure turbine (HPT) stator case (HPT case), part number (P/N)
2302M90G04 installed, and with any serial number (S/N) listed in
Table 1, 2, or 3, in the Planning Information section of GE Service
Bulletin (SB) GEnx-2B S/B 72-0360, Revision 04, dated December 4,
2018, or GE SB GEnx-1B S/B 72-0424, Revision 04, dated December 3,
2018, installed.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
section.
(e) Unsafe Condition
This AD was prompted by the discovery of a quality escape at a
manufacturing facility involving unapproved rework on HPT cases. We
are issuing this AD to prevent failure of the HPT case and
subsequent engine fire and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For HPT cases listed in Planning Information, Table 1 or 2,
of GE SB GEnx-2B S/B 72-0360, Revision 04, dated December 4, 2018,
or GE SB GEnx-1B S/B 72-0424, Revision 04, dated December 3, 2018,
determine the lesser of the following: Cycles since new (CSN) or
cycles since Class A fluorescent penetrant inspection (CSFPI) of the
entire HPT case.
(2) Using the determination made in paragraph (g)(1) of this AD,
remove from service the HPT case before exceeding the applicable
cycles in service accrued after August 15, 2018, the effective date
of AD 2018-16-07, as specified in Table 1 to paragraph (g)(2) of
this AD. Replace the removed HPT case with a part eligible for
installation.
[GRAPHIC] [TIFF OMITTED] TR08FE19.001
[[Page 2712]]
(3) For HPT cases listed in Planning Information, Table 3, of GE
SB GEnx-2B S/B 72-0360, Revision 04, dated December 4, 2018,
determine the lesser of the following: CSN or CSFPI of the entire
HPT case.
(4) Using the determination made in paragraph (g)(3) of this AD,
remove from service the HPT case before exceeding the cycles in
service specified in Table 2 to paragraph (g)(4) of this AD. Replace
the removed HPT case with a part eligible for installation.
[GRAPHIC] [TIFF OMITTED] TR08FE19.002
(5) For HPT cases listed in Planning Information, Table 3, of GE
SB GEnx-1B S/B 72-0424, Revision 04, dated December 3, 2018,
determine the lesser of the following: CSN or CSFPI of the entire
HPT case.
(6) Using the determination made in paragraph (g)(5) of this AD,
remove from service the HPT case before exceeding the cycles in
service specified in Table 3 to paragraph (g)(6) of this AD. Replace
the removed HPT case with a part eligible for installation.
[GRAPHIC] [TIFF OMITTED] TR08FE19.003
(h) Installation Prohibition
After the effective date of this AD, do not install any affected
HPT case onto any engine if the HPT case has been disassembled to
piece-part level. Affected HPT cases are identified in paragraphs
(g)(1), (g)(3), and (g)(5) of this AD. Piece-part level 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
certification office, send it to the attention of the person
identified in paragraph (j) 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 Herman Mak,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7147; 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) Service Bulletin (SB) GEnx-2B
S/B 72-0360, Revision 04, dated December 4, 2018.
(ii) GE SB GEnx-1B S/B 72-0424, Revision 04, dated December 3,
2018.
(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 the FAA, Engine and
Propeller Standards Branch, 1200 District Avenue, Burlington, MA.
For information on the availability of this material at the FAA,
call 781-238-7759.
(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.
[[Page 2713]]
Issued in Burlington, Massachusetts, on February 1, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification
Service.
[FR Doc. 2019-01589 Filed 2-7-19; 8:45 am]
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