[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:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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: <a href="/cdn-cgi/l/email-protection#127a777e6220265262653c6766713c717d7f"><span class="__cf_email__" data-cfemail="026a676e7230364272752c7776612c616d6f">[email protected]</span></a>; 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: <a href="/cdn-cgi/l/email-protection#85e1e4f3ece1abe7e0f1edeee4c5e3e4e4abe2eaf3"><span class="__cf_email__" data-cfemail="debabfa8b7baf0bcbbaab6b5bf9eb8bfbff0b9b1a8">[email protected]</span></a>.

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
----------------------------------------------------------------------------------------------------------------
ECI and visual inspection.............  14 work-hours x $85 per               $0           $1190              $0
                                         hour = $1190.
----------------------------------------------------------------------------------------------------------------

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: <a href="/cdn-cgi/l/email-protection#e6a7a8a3cba7a2cba7aba9a5a6808787c8818990"><span class="__cf_email__" data-cfemail="8bcac5cea6cacfa6cac6c4c8cbedeaeaa5ece4fd">[email protected]</span></a>.
    (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: 
<a href="/cdn-cgi/l/email-protection#1f7b7e69767b317d7a6b77747e5f797e7e31787069"><span class="__cf_email__" data-cfemail="a5c1c4d3ccc18bc7c0d1cdcec4e5c3c4c48bc2cad3">[email protected]</span></a>.

(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: <a href="/cdn-cgi/l/email-protection#9af2fff6eaa8aedaeaedb4efeef9b4f9f5f7"><span class="__cf_email__" data-cfemail="bbd3ded7cb898ffbcbcc95cecfd895d8d4d6">[email protected]</span></a>; 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]
BILLING CODE 4910-13-P


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