[Federal Register Volume 83, Number 116 (Friday, June 15, 2018)]
[Rules and Regulations]
[Pages 27891-27894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12873]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0501; Product Identifier 2018-NE-19-AD; Amendment
39-19304; AD 2018-11-16]
RIN 2120-AA64
Airworthiness Directives; Engine Alliance Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines. This
AD requires a one-time eddy current inspection (ECI) of the engine fan
hub blade slot bottom and blade slot front edge for cracks, a visual
inspection of the engine fan hub for damage, and removal of parts if
damage or defects are found that are outside serviceable limits. This
AD was prompted by an uncontained failure of the engine fan hub. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective July 2, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 2,
2018.
We must receive comments on this AD by July 30, 2018.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800-
565-0140; email: [email protected]; website:
www.engineallianceportal.com. You may view this service information at
the FAA, Engine and Propeller Standards
[[Page 27892]]
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-2018-0501.
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-2018-
0501; 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 the Docket Operations (phone:
800-647-5527) is listed above. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: David Bethka, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7129; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We received information concerning an uncontained engine fan hub
failure that occurred on an EA GP7200-series turbofan engine. AD 2017-
23-03 (82 FR 51979, November 9, 2017), requires visual inspections of
all engine fan hubs for damage. This AD requires additional visual
inspections of the EA GP7200-series engine fan hub beyond those
required by AD 2017-23-03. This AD also requires an ECI that was not
required by AD 2017-23-03. This condition, if not addressed, could
result in an uncontained failure of the engine fan hub, damage to the
engine, and damage to the airplane. We are issuing this AD to address
the unsafe condition on these products.
Related Service Information Under 1 CFR Part 51
We reviewed EA Alert Service Bulletin (ASB) EAGP7-A72-389, Revision
No. 2, dated April 17, 2018. The ASB describes procedures for ECI and
visual inspection of the GP7270, GP7272, and GP7277 engine fan hub.
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.
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 a one-time ECI of the GP7270, GP7272, and GP7277
engine fan hub blade slot bottom and blade slot front edge for cracks,
a visual inspection of the engine fan hub for damage, and removal of
the engine fan hub if damage or defects are found that are outside of
serviceable limits.
Interim Action
We consider this AD interim action. An investigation to determine
the cause of the failure is on-going and we may consider additional
rulemaking if final action is identified.
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 the adoption of this rule
because the compliance time for the required action is shorter than the
time necessary for the public to comment and for us to publish the
final rule. Therefore, we find good cause that notice and opportunity
for prior public comment are impracticable. In addition, for the reason
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-2018-
0501 and Product Identifier 2018-NE-19-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 0 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
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ECI and visual inspection............. 14 work-hours x $85 per $0 $1190 $0
hour = $1190.
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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
[[Page 27893]]
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):
2018-11-16 Engine Alliance: Amendment 39-19304 ; Docket No. FAA-
2018-0501; Product Identifier 2018-NE-19-AD.
(a) Effective Date
This AD is effective July 2, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Engine Alliance (EA) GP7270, GP7272, and
GP7277 model turbofan engines with serial numbers (S/Ns) identified
in Table 3 in Planning Information of Engine Alliance (EA) Alert
Service Bulletin (ASB) EAGP7-A72-389, Revision No. 2, dated April
17, 2018.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by an uncontained failure of the engine fan
hub. We are issuing this AD to detect defects, damage, and cracks
that could result in an uncontained failure of the engine fan hub.
The unsafe condition, if not addressed, could result in uncontained
failure of the engine fan hub, damage to the engine, and damage to
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 120 days after the effective date of this AD:
(1) For engine fan hubs at the low-pressure compressor (LPC)
module assembly level:
(i) Perform a visual inspection of the engine fan hub, in
accordance with the Accomplishment Instructions, For Fan Hubs at LPC
Module Assembly Level, paragraphs 1.A.(1), 1.A.(4), and 1.A.(6)(a),
of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(ii) Perform an eddy current inspection (ECI) of the engine fan
hub blade slot bottoms and front edges, in accordance with the
Accomplishment Instructions, For Fan Hubs at LPC Module Assembly
Level, paragraphs 2.A and 2.B, of EA ASB EAGP7-A72-389, Revision No.
2, dated April 17, 2018.
(2) For engine fan hubs at the piece part level:
(i) Perform a visual inspection of the engine fan hub, in
accordance with the Accomplishment Instructions, For Fan Hubs at
Piece Part Level, paragraphs 1.A.(1) and 1.A.(3), of EA ASB EAGP7-
A72-389, Revision No. 2, dated April 17, 2018.
(ii) Perform an ECI of the engine fan hub blade slot bottoms and
front edges, in accordance with the Accomplishment Instructions, For
Fan Hubs at Piece Part Level, paragraphs 2.A and 2.B, of EA ASB
EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(3) For engine fan hubs installed in an engine (on-wing or off-
wing):
(i) Perform a visual inspection of the engine fan hub, in
accordance with the Accomplishment Instructions, For Fan Hubs
Installed in an Engine, paragraphs 1.C.(1), 1.C.(5), and 1.C.(7)(a),
of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(ii) Perform an ECI of the engine fan hub blade slot bottoms and
front edges, in accordance with the Accomplishment Instructions, For
Fan Hubs Installed in an Engine, paragraphs 1.D.(1) and 1.D.(2), of
EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(4) If the engine fan hub visual inspection reveals defects or
damage to the engine fan hub that are found outside the serviceable
limits specified in Table 4 in the Accomplishment Instructions of EA
ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018, remove the
engine fan hub from service and replace with a part that is eligible
for installation, prior to further flight.
(5) If the fan hub ECI results in a rejectable indication, per
the Appendix, Added Data, of EA ASB EAGP7-A72-389, Revision No. 2,
dated April 17, 2018, remove the hub from service and replace with a
part that is eligible for installation, prior to further flight.
(h) Credit for Previous Actions
You may take credit for the inspection required by paragraph (g)
of this AD if you performed the inspection before the effective date
of this AD, using EA ASB EAGP7-A72-389, dated December 19, 2017, or
EA ASB EAGP7-A72-389, Revision No. 1, dated January 19, 2018.
(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 David Bethka,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7129; 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) Engine Alliance Alert Service Bulletin EAGP7-A72-389,
Revision No. 2, dated April 17, 2018.
(ii) Reserved.
(3) For Engine Alliance service information identified in this
AD, contact Engine Alliance, 411 Silver Lane, East Hartford, CT
06118; phone: 800-565-0140; email: [email protected]; website:
www.engineallianceportal.com.
(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 781-238-7759.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records
[[Page 27894]]
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 June 8, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018-12873 Filed 6-14-18; 8:45 am]
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