Airworthiness Directives; International Aero Engines Turbofan Engines, 55619-55626 [2018-24250]
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Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations
2018–22–13 Airbus SAS: Amendment 39–
19486; Docket No. FAA–2018–0908;
Product Identifier 2018–NM–136–AD.
(a) Effective Date
This AD becomes effective November 23,
2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model
A350–941 and -1041 airplanes, certificated in
any category, except those on which the
modifications specified in paragraph (c)(1) or
(c)(2) of this AD, as applicable, have been
embodied in production.
(1) Airbus modifications 113759 and
113758.
(2) Airbus modifications 113760 and
113758.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by a technical issue
detected on the inboard aileron electrohydrostatic actuators that caused potential
erroneous monitoring of those actuators. We
are issuing this AD to address possible inflight loss of inboard aileron control,
consequent increased fuel consumption due
to the resulting drag, and reduced control or
performance of the airplane if one engine is
also inoperative.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision of the Airplane Flight Manual
(AFM)
Within 30 days after the effective date of
this AD, revise the Abnormal Procedures
section of the AFM to include the
information in Airbus A350 Temporary
Revision (TR) 113, Issue 1.0, dated July 27,
2018, which introduces updated procedures
related to inboard aileron fault operations.
This may be done by inserting a copy of TR
113, Issue 1.0, dated July 27, 2018, into the
AFM. When TR 113, Issue 1.0, dated July 27,
2018, has been included in general revisions
of the AFM, the general revisions may be
inserted into the AFM, provided the relevant
information in the general revisions is
identical to that in TR 113, Issue 1.0, dated
July 27, 2018, and the TR may be removed.
Operate the airplane according to the
procedures in TR 113, Issue 1.0, dated July
27, 2018. In case any discrepancy is
identified between procedures displayed on
the electronic centralized aircraft monitoring
(ECAM) and procedures stated in the
applicable AFM, the AFM procedures
prevail.
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
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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 International Section, send it
to the attention of the person identified in
paragraph (i)(2) of this AD. Information may
be emailed to 9-ANM-116-AMOCREQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(i) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2018–0213, dated
October 1, 2018, for related information. This
MCAI may be found in the AD docket on the
internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2018–0908.
(2) For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3218.
(j) 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 this AD specifies otherwise.
(i) Airbus A350 Temporary Revision (TR)
113, Issue 1.0, dated July 27, 2018.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
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55619
telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email continuedairworthiness.a350@airbus.com; internet
https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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.
Issued in Des Moines, Washington, on
October 22, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–23991 Filed 11–6–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0431; Product
Identifier 2018–NE–16–AD; Amendment 39–
19475; AD 2018–22–02]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
International Aero Engines (IAE)
PW1133G–JM, PW1133GA–JM,
PW1130G–JM, PW1127G–JM,
PW1127GA–JM, PW1127G1–JM,
PW1124G–JM, PW1124G1–JM, and
PW1122G–JM turbofan engines with a
certain high-pressure compressor (HPC)
front hub installed. This AD was
prompted by corrosion found on the
HPC front hub. This AD requires
replacing the HPC front hub with a part
eligible for installation. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective December
12, 2018.
ADDRESSES: For service information
identified in this final rule, contact
International Aero Engines (IAE), 400
Main Street, East Hartford, CT, 06118;
phone: 800–565–0140; email: help24@
pw.utc.com; internet: https://
fleetcare.pw.utc.com. You may view this
service information at the FAA, Engine
and Propeller Standards Branch, 1200
SUMMARY:
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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–2018–0431.
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–
0431; 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:
Kevin M. Clark, Aerospace Engineer,
ECO Branch, FAA, 1200 District
Avenue, Burlington, MA, 01803; phone:
781–238–7088; fax: 781–238–7199;
email: kevin.m.clark@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to IAE PW1133G–JM,
PW1133GA–JM, PW1130G–JM,
PW1127G–JM, PW1127GA–JM,
PW1127G1–JM, PW1124G–JM,
PW1124G1–JM, and PW1122G–JM
turbofan engines with a certain HPC
front hub installed. The NPRM
published in the Federal Register on
June 28, 2018 (83 FR 30370). The NPRM
was prompted by a report that corrosion
was found on HPC front hub, part
number (P/N) 30G2401. The HPC front
hub exhibited deposits that could not be
removed using standard procedures and
worsened over time. After further
investigation, pitting corrosion was
found below the painted surface. This
condition, if not addressed, could result
in uncontained HPC front hub release,
damage to the engine, and damage to the
airplane. The NPRM proposed to require
replacing the HPC front hub with a part
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 final rule.
We have considered the comment
received on the NPRM and the FAA’s
response to each comment.
Request Clarification on CSN Limit
All Nippon Airways requested that
we clarify which cycles since new
(CSN) limit for this AD is correct. ANA
stated the PW Service Bulletin
PW1000G–C–72–00–0106–00A–930A–
D, dated June 15, 2018 specifies a limit
of 4,400 cycles since new (CSN), while
paragraph (g) of this AD specifies a limit
of 4,440 CSN.
We disagree. The AD limit of 4,440
CSN is correct. We found that 4,440
CSN provides an acceptable level of
safety, and reducing the CSN limit in
this AD to match the SB is not required.
Therefore, we did not change this AD.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this
final rule 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
We reviewed Section PW1000G–C–
05–10–00–02A–288A–D of the
PW1100G–JM Series Airworthiness
Limitations Manual, P/N 5316993, dated
September 30, 2015. Section PW1000G–
C–05–10–00–02A–288A–D provides
guidance for an approved FAA method
of mixed model cycles since new
calculation.
Costs of Compliance
We estimate that this AD affects 16
engines installed on airplanes of U.S.
registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Replace HPC front hub ...................................
0 work-hours × $85 per hour = $85 ...............
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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
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Parts cost
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.
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$11,600
Cost per
product
$11,600
Cost on U.S.
operators
$185,600
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
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(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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
AD 2018–22–02 International Aero
Engines: Amendment 39–19475; Docket
No. FAA–2018–0431; Product Identifier
2018–NE–16–AD.
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This AD applies to International Aero
Engines (IAE) PW1133G–JM, PW1133GA–JM,
PW1130G–JM, PW1127G–JM, PW1127GA–
JM, PW1127G1–JM, PW1124G–JM,
PW1124G1–JM, and PW1122G–JM turbofan
engines with a high-pressure compressor
(HPC) front hub, part number (P/N) 30G2401,
installed.
(e) Unsafe Condition
1. The authority citation for part 39
continues to read as follows:
VerDate Sep<11>2014
(c) Applicability
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
■
(a) Effective Date
This AD is effective December 12, 2018.
None.
(d) Subject
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
(b) Affected ADs
This AD was prompted by corrosion found
on the HPC front hub, P/N 30G2401,
installed. We are issuing this AD to prevent
cracking and failure of the HPC front hub.
The unsafe condition, if not addressed, could
result in uncontained HPC front hub 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
Remove from service the HPC front hub, P/
N 30G2401, within 120 days after the
effective date of this AD, or as follows,
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whichever occurs later, and replace with a
part eligible for installation:
(1) For PW1122G–JM, PW1124G1–JM,
PW1124G–JM, PW1127G1–JM, PW1127GA–
JM, and PW1127G–JM engines, remove the
HPC front hub before exceeding 6,180 cycles
since new (CSN) or within five years since
the ship date listed in Table 1 to paragraph
(g) of this AD, whichever occurs first.
(2) For PW1130G–JM, PW1133GA–JM, and
PW1133G–JM engines, remove the HPC front
hub before exceeding 4,440 CSN or within
four years since the ship date listed in Table
1 to paragraph (g) of this AD, whichever
occurs first.
(3) For engines operating as a mix of
models listed in paragraphs (g)(1) and (2) of
this AD, remove the HPC front hub using a
CSN calculated by an approved FAA method
or within four years since the ship date listed
in Table 1 to paragraph (g) of this AD,
whichever occurs first. You may find
guidance for an approved FAA method of
mixed model CSN calculation in Section
PW1000G–C–05–10–00–02A–288A–D of the
PW1100G–JM Series Airworthiness
Limitations Manual, P/N 5316993, dated
September 30, 2015.
(4) For any HPC front hub, P/N 30G2401,
whose serial number is not listed in Table 1
to paragraph (g) of this AD, use October 21,
2015, as the ship date.
BILLING CODE 4910–13–P
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Steel Front Hub Serial Number
LENCAJ3513
LENCAJ4524
LENCAJ2782
LENCAJ2794
LENCAJ4527
LENCAJ3500
LENCAJ4508
LENCAJ3505
LENCAJ4518
LENCAJ3507
LENCAJ2789
LENCAJ4516
LENCAJ3509
LENCAJ3511
LENCAJ4538
LENCAJ4535
LENCAJ2788
LENCAJ4512
LENCAJ3502
LENCAJ3503
LENCAJ4540
LENCAJ3510
LENCAJ4539
LENCAJ4525
LENCAJ4531
LENCAJ4510
LENCAJ4522
LENCAJ3506
LENCAJ4532
LENCAJ3506
LENCAJ4534
LENCAJ4548
LENCAJ4552
LENCAJ4521
LENCAJ4529
LENCAJ4520
LENCAJ4544
LENCAJ4511
LENCAJ4549
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Ship Date
10/23/2015
11/6/2015
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11/9/2015
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6/20/2016
12/2/2015
12/31/2015
12/22/2015
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12/31/2015
12/28/2015
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1/8/2016
1/17/2016
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1/31/2016
2/7/2016
1/31/2016
2/17/2016
2/14/2016
2/25/2016
2/20/2016
3/14/2016
2/27/2016
2/27/2016
3/11/2016
3/17/2016
3/3112016
6/13/2016
5/6/2016
4/30/2016
4/30/2016
4/28/2016
4/30/2016
8/25/2016
8/26/2016
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Originally Installed in
Engine Serial Number
P770121
P770125
P770126
P770127
P770128
P770129
P770130
P770131
P770132
P770133
P770134
P770135
P770136
P770137
P770138
P770139
P770140
P770141
P770142
P770143
P770144
P770145
P770146
P770147
P770148
P770149
P770150
P770151
P770153
P770154
P770155
P770160
P770161
P770163
P770164
P770165
P770166
P770167
P770168
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Table 1 to Paragraph (g) - Steel Front Hub Ship Date
LENCAJ4553
LENCAJ4551
LENCAJ4517
LENCAJ4543
LENCAJ4513
LENCAJ4550
LENCAJ4530
LENCAJ4533
LENCAJ4515
LENCAJ4563
LENCAJ4545
LENCAJ4542
LENCAJ4546
LENCAJ4566
LENCAJ4558
LENCAJ4507
LENCAK4516
LENCAJ3508
LENCAJ4572
LENCAJ4573
LENCAJ4555
LENCAJ4565
LENCAJ4559
LENCAJ4570
LENCAJ4560
LENCAJ4571
LENCAJ4562
LENCAJ4526
LENCAJ4561
LENCAJ4504
LENCAJ4579
LENCAJ4519
LENCAK4517
LENCAJ4595
LENCAK4523
LENCAK4505
LENCAJ4541
LENCAJ4592
LENCAJ4569
LENCAK4512
LENCAK4518
LENCAK4541
LENCAK4535
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P770169
P770170
P770171
P770172
P770173
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P770200
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P770207
P770208
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P770211
P770212
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LENCAJ4584
LENCAK4538
LENCAK4533
LENCAJ4594
LENCAJ4509
LENCAK4526
LENCAK4532
LENCAJ4602
LENCAK4513
LENCAK5147
LENCAK4536
LENCAK4522
LENCAJ4578
LENCAJ4596
LENCAJ4575
LENCAJ4577
LENCAJ4597
LENCAJ4588
LENCAK4552
LENCAJ4537
LENCAJ4586
LENCAJ4528
LENCAJ4554
LENCAK4553
LENCAJ4598
LENCAK4550
LENCAJ4603
LENCAJ4585
LENCAK4537
LENCAK4520
LENCAK4528
LENCAK5171
LENCAK4549
LENCAJ4557
LENCAK4515
LENCAJ4601
LENCAK4511
LENCAJ4581
LENCAK5182
LENCAK5153
LENCAJ4576
LENCAK4539
LENCAJ4591
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Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations
Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations
BILLING CODE 4910–13–C
(h) 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 (i) 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.
amozie on DSK3GDR082PROD with RULES
For more information about this AD,
contact Kevin M. Clark, Aerospace Engineer,
ECO Branch, FAA, 1200 District Avenue,
Burlington, MA, 01803; phone: 781–238–
7088; fax: 781–238–7199; email:
kevin.m.clark@faa.gov.
(j) Material Incorporated by Reference
None.
16:15 Nov 06, 2018
[Docket No. SSA–2018–0041]
The Bipartisan Budget Act of 2018 (BBA
2018) revised the MAGI ranges again for
years beginning with 2019. We consider
a beneficiary’s MAGI and tax filing
status to determine: The percentage of
the unsubsidized Medicare Part B
premium that the beneficiary must pay;
and the percentage of the cost of basic
Medicare prescription drug coverage the
beneficiary must pay. This final rule
makes our regulations consistent with
the MAGI ranges specified by MACRA
and BBA 2018.
RIN 0960–AI37
DATES:
Income-Related Monthly Adjustment
Amounts for Medicare Part B and
Prescription Drug Coverage Premiums
FOR FURTHER INFORMATION CONTACT:
[FR Doc. 2018–24250 Filed 11–6–18; 8:45 am]
BILLING CODE 4910–13–P
SOCIAL SECURITY ADMINISTRATION
20 CFR Part 418
Social Security Administration.
Final rule.
AGENCY:
(i) Related Information
VerDate Sep<11>2014
Issued in Burlington, MA, on November
01, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards
Branch, Aircraft Certification Service.
Jkt 247001
ACTION:
The Medicare Access and
CHIP Reauthorization Act of 2015
(MACRA) changed the modified
adjusted gross income (MAGI) ranges
associated with Medicare Part B and
Medicare prescription drug coverage
premiums for years beginning in 2018.
SUMMARY:
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
This rule is effective November
7, 2018.
Donald Murphy, Office of Income
Security Programs, Social Security
Administration, 6401 Security
Boulevard, Baltimore, MD 21235–6401,
(410) 965–9090. For information on
eligibility or filing for benefits, call our
national toll-free number, 1–800–772–
1213, or TTY 1–800–325–0778, or visit
our internet site, Social Security Online,
at https://www.socialsecurity.gov.
SUPPLEMENTARY INFORMATION:
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]]>Agencies
[Federal Register Volume 83, Number 216 (Wednesday, November 7, 2018)]
[Rules and Regulations]
[Pages 55619-55626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24250]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0431; Product Identifier 2018-NE-16-AD; Amendment
39-19475; AD 2018-22-02]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
International Aero Engines (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM,
PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and
PW1122G-JM turbofan engines with a certain high-pressure compressor
(HPC) front hub installed. This AD was prompted by corrosion found on
the HPC front hub. This AD requires replacing the HPC front hub with a
part eligible for installation. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective December 12, 2018.
ADDRESSES: For service information identified in this final rule,
contact International Aero Engines (IAE), 400 Main Street, East
Hartford, CT, 06118; phone: 800-565-0140; email: [email protected];
internet: https://fleetcare.pw.utc.com. You may view this service
information at the FAA, Engine and Propeller Standards Branch, 1200
[[Page 55620]]
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-2018-0431.
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-
0431; 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: Kevin M. Clark, Aerospace Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone:
781-238-7088; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to IAE PW1133G-JM, PW1133GA-
JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM,
PW1124G1-JM, and PW1122G-JM turbofan engines with a certain HPC front
hub installed. The NPRM published in the Federal Register on June 28,
2018 (83 FR 30370). The NPRM was prompted by a report that corrosion
was found on HPC front hub, part number (P/N) 30G2401. The HPC front
hub exhibited deposits that could not be removed using standard
procedures and worsened over time. After further investigation, pitting
corrosion was found below the painted surface. This condition, if not
addressed, could result in uncontained HPC front hub release, damage to
the engine, and damage to the airplane. The NPRM proposed to require
replacing the HPC front hub with a part 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 final rule. We have considered the comment received on the NPRM
and the FAA's response to each comment.
Request Clarification on CSN Limit
All Nippon Airways requested that we clarify which cycles since new
(CSN) limit for this AD is correct. ANA stated the PW Service Bulletin
PW1000G-C-72-00-0106-00A-930A-D, dated June 15, 2018 specifies a limit
of 4,400 cycles since new (CSN), while paragraph (g) of this AD
specifies a limit of 4,440 CSN.
We disagree. The AD limit of 4,440 CSN is correct. We found that
4,440 CSN provides an acceptable level of safety, and reducing the CSN
limit in this AD to match the SB is not required. Therefore, we did not
change this AD.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this final rule 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
We reviewed Section PW1000G-C-05-10-00-02A-288A-D of the PW1100G-JM
Series Airworthiness Limitations Manual, P/N 5316993, dated September
30, 2015. Section PW1000G-C-05-10-00-02A-288A-D provides guidance for
an approved FAA method of mixed model cycles since new calculation.
Costs of Compliance
We estimate that this AD affects 16 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
----------------------------------------------------------------------------------------------------------------
Replace HPC front hub................. 0 work-hours x $85 per $11,600 $11,600 $185,600
hour = $85.
----------------------------------------------------------------------------------------------------------------
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
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
[[Page 55621]]
(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):
AD 2018-22-02 International Aero Engines: Amendment 39-19475; Docket
No. FAA-2018-0431; Product Identifier 2018-NE-16-AD.
(a) Effective Date
This AD is effective December 12, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to International Aero Engines (IAE) PW1133G-JM,
PW1133GA-JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM,
PW1124G-JM, PW1124G1-JM, and PW1122G-JM turbofan engines with a
high-pressure compressor (HPC) front hub, part number (P/N) 30G2401,
installed.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by corrosion found on the HPC front hub, P/
N 30G2401, installed. We are issuing this AD to prevent cracking and
failure of the HPC front hub. The unsafe condition, if not
addressed, could result in uncontained HPC front hub 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
Remove from service the HPC front hub, P/N 30G2401, within 120
days after the effective date of this AD, or as follows, whichever
occurs later, and replace with a part eligible for installation:
(1) For PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G1-JM,
PW1127GA-JM, and PW1127G-JM engines, remove the HPC front hub before
exceeding 6,180 cycles since new (CSN) or within five years since
the ship date listed in Table 1 to paragraph (g) of this AD,
whichever occurs first.
(2) For PW1130G-JM, PW1133GA-JM, and PW1133G-JM engines, remove
the HPC front hub before exceeding 4,440 CSN or within four years
since the ship date listed in Table 1 to paragraph (g) of this AD,
whichever occurs first.
(3) For engines operating as a mix of models listed in
paragraphs (g)(1) and (2) of this AD, remove the HPC front hub using
a CSN calculated by an approved FAA method or within four years
since the ship date listed in Table 1 to paragraph (g) of this AD,
whichever occurs first. You may find guidance for an approved FAA
method of mixed model CSN calculation in Section PW1000G-C-05-10-00-
02A-288A-D of the PW1100G-JM Series Airworthiness Limitations
Manual, P/N 5316993, dated September 30, 2015.
(4) For any HPC front hub, P/N 30G2401, whose serial number is
not listed in Table 1 to paragraph (g) of this AD, use October 21,
2015, as the ship date.
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BILLING CODE 4910-13-C
(h) 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 (i) 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.
(i) Related Information
For more information about this AD, contact Kevin M. Clark,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA, 01803; phone: 781-238-7088; fax: 781-238-7199;
email: [email protected].
(j) Material Incorporated by Reference
None.
Issued in Burlington, MA, on November 01, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018-24250 Filed 11-6-18; 8:45 am]
BILLING CODE 4910-13-P
