Airworthiness Directives; Engine Alliance Turbofan Engines, 27891-27894 [2018-12873]
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Federal Register / Vol. 83, No. 116 / Friday, June 15, 2018 / Rules and Regulations
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
sradovich on DSK3GMQ082PROD with RULES
2018–13–02 Pratt & Whitney Division:
Amendment 39–19314; Docket No.
FAA–2017–0817; Product Identifier
2017–NE–30–AD.
Joint Aircraft System Component (JASC)
Code 7240, Turbine Engine Combustion
Section.
(e) Unsafe Condition
This AD was prompted by the discovery of
multiple cracked air seals. We are issuing
this AD to prevent failure of the 4th stage
LPT air seal. This unsafe condition, if not
addressed, could result in uncontained
release of the air seal, 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
The next time the 4th stage LPT vanes are
removed from the LPT module, remove 4th
stage air seal, P/N 50N346, from service and
replace with a part eligible for installation.
(h) Installation Prohibition
After the effective date of this AD, do not
install any 4th stage LPT air seal, P/N
50N346, into any LPT module.
(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: ANE-AD-AMOC@
faa.gov.
(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.
None.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Pratt & Whitney
Division (PW) PW4052, PW4056, PW4060,
Jkt 244001
For more information about this AD,
contact Jo-Ann Theriault, Aerospace
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: 781–
238–7105; fax: 781–238–7199; email: joann.theriault@faa.gov.
(k) Material Incorporated by Reference
(a) Effective Date
This AD is effective July 20, 2018.
15:57 Jun 14, 2018
(d) Subject
(j) Related Information
[Amended]
VerDate Sep<11>2014
PW4062, PW4062A, PW4152, PW4156A,
PW4158, PW4460, and PW4462 turbofan
engine models, including engines identified
with suffixes –1C, –1E, –3, –3A, or –3B, with
4th stage low-pressure turbine (LPT) air seal,
part number (P/N) 50N346, installed.
Issued in Burlington, Massachusetts, on
June 11, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards
Branch, Aircraft Certification Service.
[FR Doc. 2018–12830 Filed 6–14–18; 8:45 am]
BILLING CODE 4910–13–P
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27891
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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
https://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:
help24@pw.utc.com; website:
www.engineallianceportal.com. You
may view this service information at the
FAA, Engine and Propeller Standards
SUMMARY:
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Federal Register / Vol. 83, No. 116 / Friday, June 15, 2018 / Rules and Regulations
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 https://
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 https://
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:
david.bethka@faa.gov.
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 GP7200series 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 https://
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
Action
Labor cost
ECI and visual inspection ...............................
14 work-hours × $85 per hour = $1190 .........
sradovich on DSK3GMQ082PROD with RULES
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.
VerDate Sep<11>2014
15:57 Jun 14, 2018
Jkt 244001
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
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Cost per
product
Parts cost
$0
$1190
Cost on U.S.
operators
$0
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
E:\FR\FM\15JNR1.SGM
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Federal Register / Vol. 83, No. 116 / Friday, June 15, 2018 / Rules and Regulations
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.
of Engine Alliance (EA) Alert Service
Bulletin (ASB) EAGP7–A72–389, Revision
No. 2, dated April 17, 2018.
Regulatory Findings
(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.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
sradovich on DSK3GMQ082PROD with RULES
(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
VerDate Sep<11>2014
15:57 Jun 14, 2018
Jkt 244001
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
(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
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27893
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: ANE-AD-AMOC@
faa.gov.
(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:
david.bethka@faa.gov.
(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: help24@
pw.utc.com; 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
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Federal Register / Vol. 83, No. 116 / Friday, June 15, 2018 / Rules and Regulations
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 101
[Docket No. FDA–2018–D–1323]
The Declaration of Certain Isolated or
Synthetic Non-Digestible
Carbohydrates as Dietary Fiber on
Nutrition and Supplement Facts
Labels; Guidance for Industry;
Availability
AGENCY:
Food and Drug Administration,
HHS.
ACTION:
Notification of availability.
The Food and Drug
Administration (FDA or we) is
announcing the availability of a final
guidance for industry entitled ‘‘The
Declaration of Certain Isolated or
Synthetic Non-Digestible Carbohydrates
as Dietary Fiber on Nutrition and
Supplement Facts Labels; Guidance for
Industry.’’ The guidance identifies eight
specific, additional isolated or synthetic
non-digestible carbohydrates that we
intend to add to our regulatory
definition of ‘‘dietary fiber’’ through our
regular rulemaking process. In the
interim, the guidance also advises
manufacturers of our policy for when
one or more of these eight nondigestible carbohydrates, present in a
food, are included in the declared
amount of ‘‘dietary fiber,’’ and for the
use of a caloric value for polydextrose
of 1 kilocalorie per gram (kcal/g).
DATES: The announcement of the
guidance is published in the Federal
Register on June 15, 2018.
ADDRESSES: You may submit either
electronic or written comments on
Agency guidances at any time as
follows:
sradovich on DSK3GMQ082PROD with RULES
SUMMARY:
Electronic Submissions
Submit electronic comments in the
following way:
• Federal eRulemaking Portal:
https://www.regulations.gov. Follow the
VerDate Sep<11>2014
15:57 Jun 14, 2018
Jkt 244001
instructions for submitting comments.
Comments submitted electronically,
including attachments, to https://
www.regulations.gov will be posted to
the docket unchanged. Because your
comment will be made public, you are
solely responsible for ensuring that your
comment does not include any
confidential information that you or a
third party may not wish to be posted,
such as medical information, your or
anyone else’s Social Security number, or
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as a manufacturing process. Please note
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• If you want to submit a comment
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Submit written/paper submissions as
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well as any attachments, except for
information submitted, marked and
identified, as confidential, if submitted
as detailed in ‘‘Instructions.’’
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must include the Docket No. FDA–
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Certain Isolated or Synthetic NonDigestible Carbohydrates as Dietary
Fiber on Nutrition and Supplement
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CONFIDENTIAL INFORMATION.’’ We
will review this copy, including the
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claimed confidential information, in our
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Submit written requests for single
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document.
FOR FURTHER INFORMATION CONTACT:
Paula R. Trumbo, Center for Food Safety
and Applied Nutrition (HFS–830), Food
and Drug Administration, 5100 Campus
Dr., College Park, MD 20740, 240–402–
2579.
SUPPLEMENTARY INFORMATION:
I. Background
We are announcing the availability of
a guidance for industry entitled ‘‘The
Declaration of Certain Isolated or
Synthetic Non-Digestible Carbohydrates
as Dietary Fiber on Nutrition and
Supplement Facts Labels; Guidance for
Industry.’’ We are issuing this guidance
consistent with our good guidance
practices (GGP) regulation (§ 10.115 (21
E:\FR\FM\15JNR1.SGM
15JNR1
]]>Agencies
[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 https://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 https://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 https://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 https://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: [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: https://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
