Airworthiness Directives; General Electric Company Turbofan Engines, 53976-53979 [2018-23466]
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Federal Register / Vol. 83, No. 208 / Friday, October 26, 2018 / Rules and Regulations
(g) Required Actions
(1) For combustion cases listed in Planning
Information, Table 1, paragraph 1.A. of GE
SB GE90–100 S/B 72–0788, Revision 4, dated
July 30, 2018, except combustion cases with
S/Ns FDBK3717, FDBK3872, or FDBK4849,
remove the affected cases from service, using
the cycles specified in Table 1 to paragraph
(g) of this AD.
(2) For combustion cases with S/Ns listed
in Table 3, paragraph 1.C., Planning
Information, of GE SB GE90–100 S/B 72–
0788, Revision 4, dated July 30, 2018, remove
the affected cases from service before
exceeding the Maximum In-Service CSN
listed in Table 3, of GE SB GE90–100 S/B 72–
0788, Revision 4, dated July 30, 2018.
(3) For combustion cases with S/Ns listed
in paragraph 1.A., Planning Information, of
GE SB GE90–100 SB 72–0784 R00, dated May
4, 2018, remove the affected cases from
service within 10 cycles in service from the
effective date of this AD.
(4) For combustion cases with S/Ns listed
in Table 1, paragraph 1.A., Planning
Information, of GE SB GE90–100 SB 72–0793
R00, dated August 10, 2018, remove the
affected cases from service at the next engine
shop visit.
(5) Replace the removed combustion case
with a part eligible for installation before
further flight.
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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(h) Definitions
(1) For the purpose of this AD, an ‘‘engine
shop visit’’ is the induction of an engine into
the shop for maintenance involving the
separation of pairs of major mating engine
flanges, except that the separation of engine
flanges solely for the purposes of
transportation of the engine, without
subsequent engine maintenance, does not
constitute an engine shop visit.
(2) For the purpose of this AD, a ‘‘part
eligible for installation’’ is any combustion
case not identified in paragraph (c)(1) of this
AD or a combustion case listed in this AD
that has been inspected and repaired by a
method approved by the Manager, ECO
Branch, FAA.
(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
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18:06 Oct 25, 2018
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(j) Related Information
For more information about this AD,
contact Matthew Smith, Aerospace Engineer,
ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7735; fax: 781–238–7199; email:
matthew.c.smith@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) General Electric Company (GE) GE90–
100 Service Bulletin (SB) SB 72–0784 R00,
dated May 4, 2018.
(ii) GE SB GE90–100 S/B 72–0788,
Revision 4, dated July 30, 2018.
(iii) GE SB GE90–100 SB 72–0793 R00,
dated August 10, 2018.
(3) For service information identified in
this AD, contact General Electric Company,
GE Aviation, 1 Neumann Way, Cincinnati,
OH 45215; telephone 513–552–3272; email:
aviation.fleetsupport@ge.com.
(4) You may view this service information
at FAA, Engine and Propeller Standards
Branch, 1200 District Avenue, Burlington,
MA 01803. For information on the
availability of this material at the FAA, call
781–238–7759.
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Issued in Burlington, Massachusetts, on
October 18, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller
Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018–23468 Filed 10–25–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0406; Product
Identifier 2013–NE–30–AD; Amendment 39–
19457; AD 2018–20–23]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2017–07–
04 for General Electric Company (GE)
GE90–110B1 and GE90–115B turbofan
engines with certain high-pressure
compressor (HPC) rotor stage 2–5 spools
installed. AD 2017–07–04 required
removing certain HPC rotor stage 2–5
spools from service at times determined
by a drawdown plan. This AD requires
SUMMARY:
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Federal Register / Vol. 83, No. 208 / Friday, October 26, 2018 / Rules and Regulations
removing certain HPC rotor stage 2–5
spools from service before reaching the
new reduced life limit and replacing
them with parts eligible for installation.
This AD was prompted by the
publication of a GE service bulletin (SB)
that increases the number of affected
HPC rotor stage 2–5 spools and includes
HPC rotor stage 2–5 spools that were
inadvertently omitted from the
applicability of AD 2017–07–04. We are
issuing this AD to address the unsafe
condition on these products.
This AD is effective November
30, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 30, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of April 21, 2017 (82 FR
16728, April 6, 2017).
DATES:
For service information
identified in this final rule, contact
General Electric Company, 1 Neumann
Way, Room 285, Cincinnati, OH 45215;
phone: 513–552–3272; email: geae.aoc@
ge.com. You may view this service
information at the FAA, Engine and
Propeller Standards Branch, 1200
District Avenue, Burlington, MA 01803.
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–2018–0406.
ADDRESSES:
Examining the AD Docket
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You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0406; 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 address for Docket
Operations (phone: 800–647–5527) is
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
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:
VerDate Sep<11>2014
18:06 Oct 25, 2018
Jkt 247001
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017–07–04,
Amendment 39–18842 (82 FR 16728,
April 6, 2017), (‘‘AD 2017–07–04’’). AD
2017–07–04 applied to GE GE90–110B1
and GE90–115B turbofan engines with
certain HPC rotor stage 2–5 spools
installed. The NPRM published in the
Federal Register on June 25, 2018 (83
FR 29474). The NPRM was prompted by
the publication of a GE SB that increases
the number of affected HPC rotor stage
2–5 spools and includes HPC rotor stage
2–5 spools that were inadvertently
omitted from the applicability of AD
2017–07–04. The NPRM proposed to
require removing certain HPC rotor
stage 2–5 spools from service before
reaching the new reduced life limit and
replacing them with parts eligible for
installation. We are issuing this AD to
address the unsafe condition on these
products.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To List Additional Service
Information in Required Actions
All Nippon Airways (ANA), Azur
Aviation, and Lufthansa Technik AG
(Lufthansa) questioned why HPC rotor
stage 2–5 spools listed in paragraph (c)
of this AD, identified in GE SB GE90–
100 SB 72–0499 R01, dated February 5,
2014, are not required to be replaced in
paragraph (g) of this AD. Lufthansa
reasoned that GE SB GE90–100 SB 72–
0499 R01, dated February 5, 2014,
requires replacement of affected spools,
but this AD does not.
We disagree. Based on information
provided by GE, and to the best of our
knowledge, all HPC rotor stage 2–5
spools listed in paragraph 1.A. of GE SB
GE90–100 SB 72–0499 R01, dated
February 5, 2014, have been removed
from service. Because these HPC rotor
stage 2–5 spools have been removed
from service, we did not require their
removal under paragraph (g) of this AD.
This AD, however, includes an
installation prohibition under paragraph
(h) to prevent installation of these HPC
rotor stage 2–5 spools. We did not
change this AD.
Request To Consider a Threshold
Rework Option
FedEx Express (FedEx) requested that
certain HPC rotor stage 2–5 spools be
considered for a potential GE rework
option to extend their life beyond
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53977
allowances of this AD, before removal
from service. FedEx reasoned that GE
intends to provide a rework option that
will extend the life of HPC rotor stage
2–5 spools that are removed before
reaching 4,500 cycles. This rework
option could extend the on-wing times
for some engines.
We disagree. While GE intends to
provide a rework option to extend the
life of certain HPC rotor stage 2–5
spools, we do not require compliance
based on information that has not yet
been published. We based the
compliance on the most recently
published service information. This AD
and the associated GE service
information do not allow credit for
rework or life extensions. We did not
change this AD.
Request To Verify Applicability and
Purpose
ANA requested clarification regarding
whether the proposed AD intends to
require removing the following three (3)
HPC rotor stage 2–5 spool
configurations from service at a time
determined by this AD:
(1) HPC rotor stage 2–5 spools that use
the original seal teeth coating. (Known
as Population-1);
(2) HPC rotor stage 2–5 spools that use
the modified seal teeth coating. (Known
as Population-2); and
(3) HPC rotor stage 2–5 spools that use
the modified seal teeth coating without
inner-teeth coating. (Known as
Population-3).
We interpret ANA’s comment as
request to verify if this AD requires
removal of the HPC rotor stage 2–5
spools identified in GE SB GE90–100 SB
72–0499 R01, dated February 5, 2014;
GE SB GE90–100 SB 72–0659 R01,
dated February 18, 2016; and GE SB
GE90–100 S/B 72–0714, Revision 01,
dated February 16, 2018. ANA
commented that requirements and
actions in this AD are difficult to
understand.
The purpose of this AD is to remove
the HPC rotor stage 2–5 spools
identified in GE SB GE90–100 SB 72–
0659 R01, dated February 18, 2016, and
GE SB GE90–100 S/B 72–0714, Revision
01, dated February 16, 2018, from
service, and to prohibit the installation
of those HPC rotor stage 2–5 spools and
the HPC rotor stage 2–5 spools
identified in GE SB GE90–100 SB 72–
0499 R01, dated February 5, 2014.
Paragraphs (c) and (g) of this AD list the
affected part numbers and serial
numbers. We did not change this AD.
Support for the AD
The Air Line Pilots Association,
Boeing Company, and American
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Airlines expressed support for the
NPRM as written.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed GE SB GE90–100 SB 72–
0499 R01, dated February 5, 2014; GE
SB GE90–100 SB 72–0659 R01, dated
February 18, 2016; and GE SB GE90–100
S/B 72–0714, Revision 01, dated
February 16, 2018.
GE SB GE90–100 SB 72–0499 R01
describes procedures for identification
and removal from service of HPC rotor
stage 2–5 spools that use the original
seal tooth coating process. GE SB GE90–
100 SB 72–0659 R01 describes
procedures for identification and
removal from service of HPC rotor stage
2–5 spools that use a modified seal
tooth coating process. GE SB GE90–100
S/B 72–0714, Revision 01 describes
procedures for identification and
removal from service of HPC rotor stage
2–5 spools that use the modified seal
tooth coating process, without coating
between the seal teeth.
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.
Costs of Compliance
We estimate that this AD affects 85
engines installed on airplanes of U.S.
registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Parts cost
Paragraph (g)(1) Spools Replacement ...........
Paragraph (g)(2) Spools Replacement ...........
0 work-hours × $85 per hour = $0 .................
0 work-hours × $85 per hour = $0 .................
Regulatory Findings
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
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.
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
18:06 Oct 25, 2018
Jkt 247001
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
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$5,054,214
2,460,024
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2017–07–04, Amendment 39–18842 (82
FR 16728, April 6, 2017), and adding
the following new AD:
■
2018–20–23 General Electric Company:
Amendment 39–19457; Docket No.
FAA–2018–0406; Product Identifier
2013–NE–30–AD.
(a) Effective Date
This AD is effective November 30, 2018.
(b) Affected ADs
This AD replaces AD 2017–07–04,
Amendment 39–18842 (82 FR 16728, April 6,
2017).
(c) Applicability
This AD applies to General Electric
Company (GE) GE90–110B1 and GE90–115B
turbofan engines with HPC rotor stage 2–5
spools, with:
(1) A serial number (S/N) listed in either,
paragraph 4, Appendix A of GE Service
Bulletin (SB) No. GE90–100 SB 72–0499 R01,
dated February 5, 2014; in paragraph 4,
Appendix A of GE SB GE90–100 SB 72–0659
R01, dated February 18, 2016; or in
paragraph 4, Appendix A, of GE SB GE90–
100 S/B 72–0714, Revision 01, dated
February 16, 2018.
(2) A part number (P/N) 351–103–109–0, P/
N 351–103–110–0, P/N 351–103–147–0 or P/
N 351–103–152–0, with any S/N.
(d) Subject
1. The authority citation for part 39
continues to read as follows:
■
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$229,737
39,048
Cost on U.S.
operators
Authority: 49 U.S.C. 106(g), 40113, 44701.
Authority for This Rulemaking
VerDate Sep<11>2014
$229,737
39,048
Cost per
product
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
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Federal Register / Vol. 83, No. 208 / Friday, October 26, 2018 / Rules and Regulations
(e) Unsafe Condition
This AD was prompted by reports of cracks
in HPC rotor stage 2–5 spool aft spacer arms.
We are issuing this AD to prevent failure of
the HPC rotor stage 2–5 spools. The unsafe
condition, if not addressed, could result in
uncontained spool release, damage to the
engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Required Actions
(1) Remove from service HPC rotor stage 2–
5 spools with S/Ns listed in paragraph 4,
Appendix A, of GE SB GE90–100 SB 72–0659
R01, dated February 18, 2016, as follows, or
before further flight, whichever occurs later:
(i) For spools with fewer than 4,500 flight
cycles since new (CSN) as of April 21, 2017,
remove before exceeding 5,000 CSN.
(ii) For spools with 4,500 CSN or more but
fewer than 5,200 CSN as of April 21, 2017,
remove within 500 CIS but not to exceed
5,500 CSN.
(iii) For spools with 5,200 CSN or more but
fewer than 5,600 CSN as of April 21, 2017,
remove within 300 CIS but not to exceed
5,800 CSN.
(iv) For spools with 5,600 CSN or more but
fewer than 5,800 CSN as of April 21, 2017,
remove within 200 CIS but not to exceed
5,850 CSN.
(v) For spools with 5,800 CSN or more but
fewer than 6,000 CSN as of April 21, 2017,
remove within 50 CIS but not to exceed 6,000
CSN.
(vi) For spools with 6,000 CSN or more as
of April 21, 2017, remove before the next
flight.
(2) Remove from service HPC rotor stage 2–
5 spools listed in paragraph (c)(2) of this AD
and HPC rotor stage 2–5 spools with S/Ns
listed in paragraph 4, Appendix A, of GE SB
GE90–100 S/B 72–0714, Revision 01, dated
February 16, 2018, before exceeding 8,200
CSN, or before further flight, whichever
occurs later.
(h) Installation Prohibition
(1) After the effective date of this AD, do
not install or reinstall onto any engine, any
HPC rotor stage 2–5 spool with an S/N listed
in paragraph 4, Appendix A, of GE SB No.
GE90–100 SB 72–0499 R01, dated February
5, 2014, or paragraph 4, Appendix A, of GE
SB GE90–100 SB72–0659 R01, dated
February 18, 2016, that exceeds 5,000 CSN.
(2) After the effective date of this AD, do
not install or reinstall onto any engine, any
HPC rotor stage 2–5 spool listed in paragraph
(c)(2) of this AD, or HPC rotor stage 2–5 spool
with an S/N listed in paragraph 4, Appendix
A, of GE SB GE90–100 S/B 72–0714, Revision
01, dated February 16, 2018, that exceeds
8,200 CSN.
(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
VerDate Sep<11>2014
18:06 Oct 25, 2018
Jkt 247001
53979
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.
DEPARTMENT OF TRANSPORTATION
(j) Related Information
AGENCY:
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.
SUMMARY:
(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.
(3) The following service information was
approved for IBR on November 30, 2018.
(i) General Electric Company (GE) Service
Bulletin (SB) GE90–100 SB 72–0499 R01,
dated February 5, 2014.
(ii) GE SB GE90–100 S/B 72–0714,
Revision 01, dated February 16, 2018.
(4) The following service information was
approved for IBR on April 21, 2017 (82 FR
16728, April 6, 2017).
(i) GE SB GE90–100 SB 72–0659 R01, dated
February 18, 2016.
(ii) [Reserved.]
(5) For service information identified in
this AD, contact General Electric Company,
1 Neumann Way, Room 285, Cincinnati, OH
45215; phone: 513–552–3272; email:
geae.aoc@ge.com.
(6) You may view this service information
at FAA, Engine and Propeller Standards
Branch, 1200 District Avenue, Burlington,
MA 01803. For information on the
availability of this material at the FAA, call
781–238–7759.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
October 17, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller
Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018–23466 Filed 10–25–18; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2018–0094; Airspace
Docket No. 18–ASW–4]
RIN 2120–AA66
Amendment of Class D Airspace;
Tulsa, OK
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
This action amends Class D
airspace designated as an extension at
Tulsa Lloyd Jones Jr. Airport, Tulsa, OK.
This action is a result of an airspace
review caused by the decommissioning
of the Glenpool VHF omnidirectional
range (VOR) navigation aid as part of the
VOR Minimum Operational Newtork
(MON) Program and the cancellation of
the associated instrument procedures.
The geographic coordinates of the
airport are also updated; to coincide
with the FAA’s aeronautical database, as
well as an editorial change removing the
city associated with the airport name in
the airspace legal description. Also, the
outdated term ‘‘Airport/Facility
Directory’’ is replaced with ‘‘Chart
Supplement’’.
DATES: Effective 0901 UTC, January 3,
2019. The Director of the Federal
Register approves this incorporation by
reference action under Title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.11 and publication of conforming
amendments.
ADDRESSES: FAA Order 7400.11C,
Airspace Designations and Reporting
Points, and subsequent amendments can
be viewed online at https://www.faa.gov/
air_traffic/publications/. For further
information, you can contact the
Airspace Policy Group, Federal Aviation
Administration, 800 Independence
Avenue SW, Washington, DC 20591;
telephone: (202) 267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11C at NARA, call (202)
741–6030, or go to https://
www.archives.gov/federal-register/cfr/
ibr-locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT:
Rebecca Shelby, Federal Aviation
Administration, Operations Support
E:\FR\FM\26OCR1.SGM
26OCR1
]]>Agencies
[Federal Register Volume 83, Number 208 (Friday, October 26, 2018)]
[Rules and Regulations]
[Pages 53976-53979]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-23466]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0406; Product Identifier 2013-NE-30-AD; Amendment
39-19457; AD 2018-20-23]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2017-07-04 for
General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines
with certain high-pressure compressor (HPC) rotor stage 2-5 spools
installed. AD 2017-07-04 required removing certain HPC rotor stage 2-5
spools from service at times determined by a drawdown plan. This AD
requires
[[Page 53977]]
removing certain HPC rotor stage 2-5 spools from service before
reaching the new reduced life limit and replacing them with parts
eligible for installation. This AD was prompted by the publication of a
GE service bulletin (SB) that increases the number of affected HPC
rotor stage 2-5 spools and includes HPC rotor stage 2-5 spools that
were inadvertently omitted from the applicability of AD 2017-07-04. We
are issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective November 30, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 30,
2018.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of April
21, 2017 (82 FR 16728, April 6, 2017).
ADDRESSES: For service information identified in this final rule,
contact General Electric Company, 1 Neumann Way, Room 285, Cincinnati,
OH 45215; phone: 513-552-3272; email: [email protected]. You may view
this service information at the FAA, Engine and Propeller Standards
Branch, 1200 District Avenue, Burlington, MA 01803. 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-2018-0406.
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-
0406; 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 address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
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 issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017-07-04, Amendment 39-18842 (82 FR 16728,
April 6, 2017), (``AD 2017-07-04''). AD 2017-07-04 applied to GE GE90-
110B1 and GE90-115B turbofan engines with certain HPC rotor stage 2-5
spools installed. The NPRM published in the Federal Register on June
25, 2018 (83 FR 29474). The NPRM was prompted by the publication of a
GE SB that increases the number of affected HPC rotor stage 2-5 spools
and includes HPC rotor stage 2-5 spools that were inadvertently omitted
from the applicability of AD 2017-07-04. The NPRM proposed to require
removing certain HPC rotor stage 2-5 spools from service before
reaching the new reduced life limit and replacing them with parts
eligible for installation. We are issuing this AD to address the unsafe
condition on these products.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To List Additional Service Information in Required Actions
All Nippon Airways (ANA), Azur Aviation, and Lufthansa Technik AG
(Lufthansa) questioned why HPC rotor stage 2-5 spools listed in
paragraph (c) of this AD, identified in GE SB GE90-100 SB 72-0499 R01,
dated February 5, 2014, are not required to be replaced in paragraph
(g) of this AD. Lufthansa reasoned that GE SB GE90-100 SB 72-0499 R01,
dated February 5, 2014, requires replacement of affected spools, but
this AD does not.
We disagree. Based on information provided by GE, and to the best
of our knowledge, all HPC rotor stage 2-5 spools listed in paragraph
1.A. of GE SB GE90-100 SB 72-0499 R01, dated February 5, 2014, have
been removed from service. Because these HPC rotor stage 2-5 spools
have been removed from service, we did not require their removal under
paragraph (g) of this AD. This AD, however, includes an installation
prohibition under paragraph (h) to prevent installation of these HPC
rotor stage 2-5 spools. We did not change this AD.
Request To Consider a Threshold Rework Option
FedEx Express (FedEx) requested that certain HPC rotor stage 2-5
spools be considered for a potential GE rework option to extend their
life beyond allowances of this AD, before removal from service. FedEx
reasoned that GE intends to provide a rework option that will extend
the life of HPC rotor stage 2-5 spools that are removed before reaching
4,500 cycles. This rework option could extend the on-wing times for
some engines.
We disagree. While GE intends to provide a rework option to extend
the life of certain HPC rotor stage 2-5 spools, we do not require
compliance based on information that has not yet been published. We
based the compliance on the most recently published service
information. This AD and the associated GE service information do not
allow credit for rework or life extensions. We did not change this AD.
Request To Verify Applicability and Purpose
ANA requested clarification regarding whether the proposed AD
intends to require removing the following three (3) HPC rotor stage 2-5
spool configurations from service at a time determined by this AD:
(1) HPC rotor stage 2-5 spools that use the original seal teeth
coating. (Known as Population-1);
(2) HPC rotor stage 2-5 spools that use the modified seal teeth
coating. (Known as Population-2); and
(3) HPC rotor stage 2-5 spools that use the modified seal teeth
coating without inner-teeth coating. (Known as Population-3).
We interpret ANA's comment as request to verify if this AD requires
removal of the HPC rotor stage 2-5 spools identified in GE SB GE90-100
SB 72-0499 R01, dated February 5, 2014; GE SB GE90-100 SB 72-0659 R01,
dated February 18, 2016; and GE SB GE90-100 S/B 72-0714, Revision 01,
dated February 16, 2018. ANA commented that requirements and actions in
this AD are difficult to understand.
The purpose of this AD is to remove the HPC rotor stage 2-5 spools
identified in GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016,
and GE SB GE90-100 S/B 72-0714, Revision 01, dated February 16, 2018,
from service, and to prohibit the installation of those HPC rotor stage
2-5 spools and the HPC rotor stage 2-5 spools identified in GE SB GE90-
100 SB 72-0499 R01, dated February 5, 2014. Paragraphs (c) and (g) of
this AD list the affected part numbers and serial numbers. We did not
change this AD.
Support for the AD
The Air Line Pilots Association, Boeing Company, and American
[[Page 53978]]
Airlines expressed support for the NPRM as written.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed GE SB GE90-100 SB 72-0499 R01, dated February 5, 2014;
GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016; and GE SB GE90-
100 S/B 72-0714, Revision 01, dated February 16, 2018.
GE SB GE90-100 SB 72-0499 R01 describes procedures for
identification and removal from service of HPC rotor stage 2-5 spools
that use the original seal tooth coating process. GE SB GE90-100 SB 72-
0659 R01 describes procedures for identification and removal from
service of HPC rotor stage 2-5 spools that use a modified seal tooth
coating process. GE SB GE90-100 S/B 72-0714, Revision 01 describes
procedures for identification and removal from service of HPC rotor
stage 2-5 spools that use the modified seal tooth coating process,
without coating between the seal teeth.
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.
Costs of Compliance
We estimate that this AD affects 85 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
----------------------------------------------------------------------------------------------------------------
Paragraph (g)(1) Spools Replacement... 0 work-hours x $85 per $229,737 $229,737 $5,054,214
hour = $0.
Paragraph (g)(2) Spools Replacement... 0 work-hours x $85 per 39,048 39,048 2,460,024
hour = $0.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2017-07-04, Amendment 39-18842 (82 FR 16728, April 6, 2017), and adding
the following new AD:
2018-20-23 General Electric Company: Amendment 39-19457; Docket No.
FAA-2018-0406; Product Identifier 2013-NE-30-AD.
(a) Effective Date
This AD is effective November 30, 2018.
(b) Affected ADs
This AD replaces AD 2017-07-04, Amendment 39-18842 (82 FR 16728,
April 6, 2017).
(c) Applicability
This AD applies to General Electric Company (GE) GE90-110B1 and
GE90-115B turbofan engines with HPC rotor stage 2-5 spools, with:
(1) A serial number (S/N) listed in either, paragraph 4,
Appendix A of GE Service Bulletin (SB) No. GE90-100 SB 72-0499 R01,
dated February 5, 2014; in paragraph 4, Appendix A of GE SB GE90-100
SB 72-0659 R01, dated February 18, 2016; or in paragraph 4, Appendix
A, of GE SB GE90-100 S/B 72-0714, Revision 01, dated February 16,
2018.
(2) A part number (P/N) 351-103-109-0, P/N 351-103-110-0, P/N
351-103-147-0 or P/N 351-103-152-0, with any S/N.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
[[Page 53979]]
(e) Unsafe Condition
This AD was prompted by reports of cracks in HPC rotor stage 2-5
spool aft spacer arms. We are issuing this AD to prevent failure of
the HPC rotor stage 2-5 spools. The unsafe condition, if not
addressed, could result in uncontained spool release, 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
(1) Remove from service HPC rotor stage 2-5 spools with S/Ns
listed in paragraph 4, Appendix A, of GE SB GE90-100 SB 72-0659 R01,
dated February 18, 2016, as follows, or before further flight,
whichever occurs later:
(i) For spools with fewer than 4,500 flight cycles since new
(CSN) as of April 21, 2017, remove before exceeding 5,000 CSN.
(ii) For spools with 4,500 CSN or more but fewer than 5,200 CSN
as of April 21, 2017, remove within 500 CIS but not to exceed 5,500
CSN.
(iii) For spools with 5,200 CSN or more but fewer than 5,600 CSN
as of April 21, 2017, remove within 300 CIS but not to exceed 5,800
CSN.
(iv) For spools with 5,600 CSN or more but fewer than 5,800 CSN
as of April 21, 2017, remove within 200 CIS but not to exceed 5,850
CSN.
(v) For spools with 5,800 CSN or more but fewer than 6,000 CSN
as of April 21, 2017, remove within 50 CIS but not to exceed 6,000
CSN.
(vi) For spools with 6,000 CSN or more as of April 21, 2017,
remove before the next flight.
(2) Remove from service HPC rotor stage 2-5 spools listed in
paragraph (c)(2) of this AD and HPC rotor stage 2-5 spools with S/Ns
listed in paragraph 4, Appendix A, of GE SB GE90-100 S/B 72-0714,
Revision 01, dated February 16, 2018, before exceeding 8,200 CSN, or
before further flight, whichever occurs later.
(h) Installation Prohibition
(1) After the effective date of this AD, do not install or
reinstall onto any engine, any HPC rotor stage 2-5 spool with an S/N
listed in paragraph 4, Appendix A, of GE SB No. GE90-100 SB 72-0499
R01, dated February 5, 2014, or paragraph 4, Appendix A, of GE SB
GE90-100 SB72-0659 R01, dated February 18, 2016, that exceeds 5,000
CSN.
(2) After the effective date of this AD, do not install or
reinstall onto any engine, any HPC rotor stage 2-5 spool listed in
paragraph (c)(2) of this AD, or HPC rotor stage 2-5 spool with an S/
N listed in paragraph 4, Appendix A, of GE SB GE90-100 S/B 72-0714,
Revision 01, dated February 16, 2018, that exceeds 8,200 CSN.
(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.
(3) The following service information was approved for IBR on
November 30, 2018.
(i) General Electric Company (GE) Service Bulletin (SB) GE90-100
SB 72-0499 R01, dated February 5, 2014.
(ii) GE SB GE90-100 S/B 72-0714, Revision 01, dated February 16,
2018.
(4) The following service information was approved for IBR on
April 21, 2017 (82 FR 16728, April 6, 2017).
(i) GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016.
(ii) [Reserved.]
(5) For service information identified in this AD, contact
General Electric Company, 1 Neumann Way, Room 285, Cincinnati, OH
45215; phone: 513-552-3272; email: [email protected].
(6) You may view this service information at FAA, Engine and
Propeller Standards Branch, 1200 District Avenue, Burlington, MA
01803. For information on the availability of this material at the
FAA, call 781-238-7759.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on October 17, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller Standards Branch, Aircraft
Certification Service.
[FR Doc. 2018-23466 Filed 10-25-18; 8:45 am]
BILLING CODE 4910-13-P
