83 FR 27891 - Airworthiness Directives; Engine Alliance Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 116 (June 15, 2018)

Page Range		27891-27894
FR Document		2018-12873

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.

Federal Register, Volume 83 Issue 116 (Friday, June 15, 2018)

[Federal Register Volume 83, Number 116 (Friday, June 15, 2018)]
[Rules and Regulations]
[Pages 27891-27894]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2018-12873]

-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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: help24@pw.utc.com; 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: 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 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.

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: 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

[[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

Federal Register / Vol. 83, No. 116 / Friday, June 15, 2018 / Rules and Regulations 27891

of ADs is normally a function of the PW4062, PW4062A, PW4152, PW4156A, DEPARTMENT OF TRANSPORTATION
Compliance and Airworthiness PW4158, PW4460, and PW4462 turbofan
Division, but during this transition engine models, including engines identified Federal Aviation Administration
period, the Executive Director has with suffixes –1C, –1E, –3, –3A, or –3B, with
4th stage low-pressure turbine (LPT) air seal, 14 CFR Part 39
delegated the authority to issue ADs
part number (P/N) 50N346, installed.
applicable to engines, propellers, and [Docket No. FAA–2018–0501; Product
associated appliances to the Manager, (d) Subject Identifier 2018–NE–19–AD; Amendment 39–
Engine and Propeller Standards Branch, Joint Aircraft System Component (JASC) 19304; AD 2018–11–16]
Policy and Innovation Division. Code 7240, Turbine Engine Combustion
Section. RIN 2120–AA64
Regulatory Findings
This AD will not have federalism (e) Unsafe Condition Airworthiness Directives; Engine
implications under Executive Order This AD was prompted by the discovery of Alliance Turbofan Engines
13132. This AD will not have a multiple cracked air seals. We are issuing
AGENCY: Federal Aviation
substantial direct effect on the States, on this AD to prevent failure of the 4th stage
LPT air seal. This unsafe condition, if not
Administration (FAA), DOT.
the relationship between the national ACTION: Final rule; request for
addressed, could result in uncontained
government and the States, or on the release of the air seal, damage to the engine, comments.
distribution of power and and damage to the airplane.
responsibilities among the various SUMMARY: We are adopting a new
levels of government. (f) Compliance airworthiness directive (AD) for certain
For the reasons discussed above, I Comply with this AD within the Engine Alliance (EA) GP7270, GP7272,
certify that this AD: compliance times specified, unless already and GP7277 turbofan engines. This AD
(1) Is not a ‘‘significant regulatory done. requires a one-time eddy current
action’’ under Executive Order 12866, (g) Required Actions inspection (ECI) of the engine fan hub
(2) Is not a ‘‘significant rule’’ under blade slot bottom and blade slot front
DOT Regulatory Policies and Procedures The next time the 4th stage LPT vanes are
removed from the LPT module, remove 4th edge for cracks, a visual inspection of
(44 FR 11034, February 26, 1979), the engine fan hub for damage, and
(3) Will not affect intrastate aviation stage air seal, P/N 50N346, from service and
replace with a part eligible for installation. removal of parts if damage or defects are
in Alaska and found that are outside serviceable
(4) Will not have a significant (h) Installation Prohibition
limits. This AD was prompted by an
economic impact, positive or negative, After the effective date of this AD, do not uncontained failure of the engine fan
on a substantial number of small entities install any 4th stage LPT air seal, P/N hub. We are issuing this AD to address
under the criteria of the Regulatory 50N346, into any LPT module. the unsafe condition on these products.
Flexibility Act.
(i) Alternative Methods of Compliance DATES: This AD is effective July 2, 2018.
List of Subjects in 14 CFR Part 39 (AMOCs) The Director of the Federal Register
Air transportation, Aircraft, Aviation (1) The Manager, ECO Branch, FAA, has approved the incorporation by reference
safety, Incorporation by reference, the authority to approve AMOCs for this AD, of a certain publication listed in this AD
Safety. if requested using the procedures found in 14 as of July 2, 2018.
CFR 39.19. In accordance with 14 CFR 39.19, We must receive comments on this
Adoption of the Amendment send your request to your principal inspector AD by July 30, 2018.
Accordingly, under the authority or local flight standards district office, as
appropriate. If sending information directly ADDRESSES: You may send comments,
delegated to me by the Administrator, using the procedures found in 14 CFR
to the manager of the certification office,
the FAA amends 14 CFR part 39 as send it to the attention of the person 11.43 and 11.45, by any of the following
follows: identified in paragraph (j) of this AD. You methods:
may email your request to: ANE-AD-AMOC@ • Federal eRulemaking Portal: Go to
PART 39—AIRWORTHINESS faa.gov. http://www.regulations.gov. Follow the
DIRECTIVES (2) Before using any approved AMOC, instructions for submitting comments.
■ 1. The authority citation for part 39
notify your appropriate principal inspector, • Fax: 202–493–2251.
continues to read as follows:
or lacking a principal inspector, the manager • Mail: U.S. Department of
of the local flight standards district office/ Transportation, Docket Operations, M–
Authority: 49 U.S.C. 106(g), 40113, 44701. certificate holding district office.
30, West Building Ground Floor, Room
§ 39.13 [Amended] (j) Related Information W12–140, 1200 New Jersey Avenue SE,
For more information about this AD, Washington, DC 20590.
■ 2. The FAA amends § 39.13 by adding
contact Jo-Ann Theriault, Aerospace • Hand Delivery: U.S. Department of
the following new airworthiness
Engineer, ECO Branch, FAA, 1200 District Transportation, Docket Operations, M–
directive (AD):
Avenue, Burlington, MA 01803; phone: 781– 30, West Building Ground Floor, Room
2018–13–02 Pratt & Whitney Division: 238–7105; fax: 781–238–7199; email: jo- W12–140, 1200 New Jersey Avenue SE,
Amendment 39–19314; Docket No. ann.theriault@faa.gov. Washington, DC 20590, between 9 a.m.
FAA–2017–0817; Product Identifier
2017–NE–30–AD. (k) Material Incorporated by Reference and 5 p.m., Monday through Friday,
None.
except Federal holidays.
(a) Effective Date For service information identified in
sradovich on DSK3GMQ082PROD with RULES

This AD is effective July 20, 2018. Issued in Burlington, Massachusetts, on this final rule, contact Engine Alliance,
June 11, 2018. 411 Silver Lane, East Hartford, CT
(b) Affected ADs
Robert J. Ganley, 06118; phone: 800–565–0140; email:
None. Manager, Engine and Propeller Standards help24@pw.utc.com; website:
(c) Applicability Branch, Aircraft Certification Service. www.engineallianceportal.com. You
This AD applies to all Pratt & Whitney [FR Doc. 2018–12830 Filed 6–14–18; 8:45 am] may view this service information at the
Division (PW) PW4052, PW4056, PW4060, BILLING CODE 4910–13–P FAA, Engine and Propeller Standards

VerDate Sep<11>2014 15:57 Jun 14, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\15JNR1.SGM 15JNR1

27892 Federal Register / Vol. 83, No. 116 / Friday, June 15, 2018 / Rules and Regulations

Branch, 1200 District Avenue, damage to the airplane. We are issuing The FAA has found that the risk to the
Burlington, MA. For information on the this AD to address the unsafe condition flying public justifies waiving notice
availability of this material at the FAA, on these products. and comment prior to the adoption of
call 781–238–7759. It is also available this rule because the compliance time
Related Service Information Under 1
on the internet at http:// for the required action is shorter than
CFR Part 51
www.regulations.gov by searching for the time necessary for the public to
and locating Docket No. FAA–2018– We reviewed EA Alert Service comment and for us to publish the final
0501. Bulletin (ASB) EAGP7–A72–389, rule. Therefore, we find good cause that
Revision No. 2, dated April 17, 2018. notice and opportunity for prior public
Examining the AD Docket
The ASB describes procedures for ECI comment are impracticable. In addition,
You may examine the AD docket on and visual inspection of the GP7270, for the reason stated above, we find that
the internet at http:// GP7272, and GP7277 engine fan hub. good cause exists for making this
www.regulations.gov by searching for This service information is reasonably amendment effective in less than 30
and locating Docket No. FAA–2018– available because the interested parties days.
0501; or in person at Docket Operations have access to it through their normal
between 9 a.m. and 5 p.m., Monday course of business or by the means Comments Invited
through Friday, except Federal holidays. identified in the ADDRESSES section. This AD is a final rule that involves
The AD docket contains this final rule, requirements affecting flight safety and
the regulatory evaluation, any FAA’s Determination
was not preceded by notice and an
comments received, and other We are issuing this AD because we opportunity for public comment.
information. The street address for the evaluated all the relevant information However, we invite you to send any
Docket Operations (phone: 800–647– and determined the unsafe condition written data, views, or arguments about
5527) is listed above. Comments will be described previously is likely to exist or this final rule. Send your comments to
available in the AD docket shortly after develop in other products of the same an address listed under the ADDRESSES
receipt. type design. section. Include the docket number
FOR FURTHER INFORMATION CONTACT:
AD Requirements FAA–2018–0501 and Product Identifier
David Bethka, Aerospace Engineer, ECO 2018–NE–19–AD at the beginning of
Branch, FAA, 1200 District Avenue, This AD requires a one-time ECI of your comments. We specifically invite
Burlington, MA 01803; phone: 781– the GP7270, GP7272, and GP7277 comments on the overall regulatory,
238–7129; fax: 781–238–7199; email: engine fan hub blade slot bottom and economic, environmental, and energy
david.bethka@faa.gov. blade slot front edge for cracks, a visual aspects of this final rule. We will
SUPPLEMENTARY INFORMATION: inspection of the engine fan hub for consider all comments received by the
damage, and removal of the engine fan closing date and may amend this final
Discussion
hub if damage or defects are found that rule because of those comments.
We received information concerning are outside of serviceable limits.
an uncontained engine fan hub failure We will post all comments we
that occurred on an EA GP7200-series Interim Action receive, without change, to http://
turbofan engine. AD 2017–23–03 (82 FR We consider this AD interim action. www.regulations.gov, including any
51979, November 9, 2017), requires An investigation to determine the cause personal information you provide. We
visual inspections of all engine fan hubs of the failure is on-going and we may will also post a report summarizing each
for damage. This AD requires additional consider additional rulemaking if final substantive verbal contact we receive
visual inspections of the EA GP7200- action is identified. about this final rule.
series engine fan hub beyond those Costs of Compliance
required by AD 2017–23–03. This AD FAA’s Justification and Determination
also requires an ECI that was not of the Effective Date We estimate that this AD affects 0
required by AD 2017–23–03. This An unsafe condition exists that engines installed on airplanes of U.S.
condition, if not addressed, could result requires the immediate adoption of this registry.
in an uncontained failure of the engine AD without providing an opportunity We estimate the following costs to
fan hub, damage to the engine, and for public comments prior to adoption. 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 × $85 per hour = $1190 ......... $0 $1190 $0

Authority for This Rulemaking We are issuing this rulemaking under because it addresses an unsafe condition
the authority described in Subtitle VII, that is likely to exist or develop on
Title 49 of the United States Code Part A, Subpart III, Section 44701: products identified in this rulemaking
specifies the FAA’s authority to issue ‘‘General requirements.’’ Under that action.
sradovich on DSK3GMQ082PROD with RULES

rules on aviation safety. Subtitle I, section, Congress charges the FAA with This AD is issued in accordance with
section 106, describes the authority of promoting safe flight of civil aircraft in authority delegated by the Executive
the FAA Administrator. ‘‘Subtitle VII: air commerce by prescribing regulations Director, Aircraft Certification Service,
Aviation Programs’’ describes in more for practices, methods, and procedures as authorized by FAA Order 8000.51C.
detail the scope of the Agency’s the Administrator finds necessary for In accordance with that order, issuance
authority. safety in air commerce. This regulation of ADs is normally a function of the
is within the scope of that authority Compliance and Airworthiness

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Federal Register / Vol. 83, No. 116 / Friday, June 15, 2018 / Rules and Regulations 27893

Division, but during this transition of Engine Alliance (EA) Alert Service limits specified in Table 4 in the
period, the Executive Director has Bulletin (ASB) EAGP7–A72–389, Revision Accomplishment Instructions of EA ASB
delegated the authority to issue ADs No. 2, dated April 17, 2018. EAGP7–A72–389, Revision No. 2, dated
April 17, 2018, remove the engine fan hub
applicable to engines, propellers, and (d) Subject from service and replace with a part that is
associated appliances to the Manager, Joint Aircraft System Component (JASC) eligible for installation, prior to further flight.
Engine and Propeller Standards Branch, Code 7230, Turbine Engine Compressor (5) If the fan hub ECI results in a rejectable
Policy and Innovation Division. Section. indication, per the Appendix, Added Data, of
EA ASB EAGP7–A72–389, Revision No. 2,
Regulatory Findings (e) Unsafe Condition
dated April 17, 2018, remove the hub from
This AD will not have federalism This AD was prompted by an uncontained service and replace with a part that is eligible
implications under Executive Order failure of the engine fan hub. We are issuing for installation, prior to further flight.
this AD to detect defects, damage, and cracks
13132. This AD will not have a that could result in an uncontained failure of (h) Credit for Previous Actions
substantial direct effect on the States, on the engine fan hub. The unsafe condition, if You may take credit for the inspection
the relationship between the national not addressed, could result in uncontained required by paragraph (g) of this AD if you
government and the States, or on the failure of the engine fan hub, damage to the performed the inspection before the effective
distribution of power and engine, and damage to the airplane. date of this AD, using EA ASB EAGP7–A72–
responsibilities among the various 389, dated December 19, 2017, or EA ASB
(f) Compliance
levels of government. EAGP7–A72–389, Revision No. 1, dated
Comply with this AD within the January 19, 2018.
For the reasons discussed above, I compliance times specified, unless already
certify that this AD: done. (i) Alternative Methods of Compliance
(1) Is not a ‘‘significant regulatory (AMOCs)
action’’ under Executive Order 12866, (g) Required Actions
(1) The Manager, ECO Branch, FAA, has
(2) Is not a ‘‘significant rule’’ under Within 120 days after the effective date of the authority to approve AMOCs for this AD,
DOT Regulatory Policies and Procedures this AD: if requested using the procedures found in 14
(44 FR 11034, February 26, 1979), (1) For engine fan hubs at the low-pressure CFR 39.19. In accordance with 14 CFR 39.19,
compressor (LPC) module assembly level: send your request to your principal inspector
(3) Will not affect intrastate aviation (i) Perform a visual inspection of the
in Alaska, and or local Flight Standards District Office, as
engine fan hub, in accordance with the appropriate. If sending information directly
(4) Will not have a significant Accomplishment Instructions, For Fan Hubs to the manager of the certification office,
economic impact, positive or negative, at LPC Module Assembly Level, paragraphs send it to the attention of the person
on a substantial number of small entities 1.A.(1), 1.A.(4), and 1.A.(6)(a), of EA ASB identified in paragraph (j) of this AD. You
under the criteria of the Regulatory EAGP7–A72–389, Revision No. 2, dated may email your request to: ANE-AD-AMOC@
Flexibility Act. April 17, 2018. faa.gov.
(ii) Perform an eddy current inspection (2) Before using any approved AMOC,
List of Subjects in 14 CFR Part 39 (ECI) of the engine fan hub blade slot bottoms notify your appropriate principal inspector,
and front edges, in accordance with the or lacking a principal inspector, the manager
Air transportation, Aircraft, Aviation Accomplishment Instructions, For Fan Hubs of the local flight standards district office/
safety, Incorporation by reference, at LPC Module Assembly Level, paragraphs certificate holding district office.
Safety. 2.A and 2.B, of EA ASB EAGP7–A72–389,
Revision No. 2, dated April 17, 2018. (j) Related Information
Adoption of the Amendment
(2) For engine fan hubs at the piece part For more information about this AD,
Accordingly, under the authority level: contact David Bethka, Aerospace Engineer,
delegated to me by the Administrator, (i) Perform a visual inspection of the ECO Branch, FAA, 1200 District Avenue,
the FAA amends 14 CFR part 39 as engine fan hub, in accordance with the Burlington, MA 01803; phone: 781–238–
follows: Accomplishment Instructions, For Fan Hubs 7129; fax: 781–238–7199; email:
at Piece Part Level, paragraphs 1.A.(1) and david.bethka@faa.gov.
PART 39—AIRWORTHINESS 1.A.(3), of EA ASB EAGP7–A72–389,
Revision No. 2, dated April 17, 2018. (k) Material Incorporated by Reference
DIRECTIVES (ii) Perform an ECI of the engine fan hub (1) The Director of the Federal Register
blade slot bottoms and front edges, in approved the incorporation by reference
■ 1. The authority citation for part 39 accordance with the Accomplishment (IBR) of the service information listed in this
continues to read as follows: Instructions, For Fan Hubs at Piece Part paragraph under 5 U.S.C. 552(a) and 1 CFR
Authority: 49 U.S.C. 106(g), 40113, 44701. Level, paragraphs 2.A and 2.B, of EA ASB part 51.
EAGP7–A72–389, Revision No. 2, dated (2) You must use this service information
§ 39.13 [Amended] April 17, 2018. as applicable to do the actions required by
(3) For engine fan hubs installed in an this AD, unless the AD specifies otherwise.
■ 2. The FAA amends § 39.13 by adding engine (on-wing or off-wing): (i) Engine Alliance Alert Service Bulletin
the following new airworthiness (i) Perform a visual inspection of the EAGP7–A72–389, Revision No. 2, dated
directive (AD): engine fan hub, in accordance with the April 17, 2018.
2018–11–16 Engine Alliance: Amendment Accomplishment Instructions, For Fan Hubs (ii) Reserved.
39–19304 ; Docket No. FAA–2018–0501; Installed in an Engine, paragraphs 1.C.(1), (3) For Engine Alliance service information
Product Identifier 2018–NE–19–AD. 1.C.(5), and 1.C.(7)(a), of EA ASB EAGP7– identified in this AD, contact Engine
A72–389, Revision No. 2, dated April 17, Alliance, 411 Silver Lane, East Hartford, CT
(a) Effective Date 2018. 06118; phone: 800–565–0140; email: help24@
This AD is effective July 2, 2018. (ii) Perform an ECI of the engine fan hub pw.utc.com; website:
blade slot bottoms and front edges, in www.engineallianceportal.com.
(b) Affected ADs
sradovich on DSK3GMQ082PROD with RULES

accordance with the Accomplishment (4) You may view this service information
None. Instructions, For Fan Hubs Installed in an at FAA, Engine and Propeller Standards
Engine, paragraphs 1.D.(1) and 1.D.(2), of EA Branch, 1200 District Avenue, Burlington,
(c) Applicability ASB EAGP7–A72–389, Revision No. 2, dated MA. For information on the availability of
This AD applies to Engine Alliance (EA) April 17, 2018. this material at the FAA, call 781–238–7759.
GP7270, GP7272, and GP7277 model (4) If the engine fan hub visual inspection (5) You may view this service information
turbofan engines with serial numbers (S/Ns) reveals defects or damage to the engine fan that is incorporated by reference at the
identified in Table 3 in Planning Information hub that are found outside the serviceable National Archives and Records

VerDate Sep<11>2014 15:57 Jun 14, 2018 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\15JNR1.SGM 15JNR1

Document Created: 2018-11-02 12:00:53
Document Modified: 2018-11-02 12:00:53

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule; request for comments.
Dates		This AD is effective July 2, 2018.
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]
FR Citation		83 FR 27891
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

83 FR 27891 - Airworthiness Directives; Engine Alliance Turbofan Engines

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 116 (June 15, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration