[Federal Register Volume 83, Number 125 (Thursday, June 28, 2018)]
[Proposed Rules]
[Pages 30370-30377]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-13795]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0431; Product Identifier 2018-NE-16-AD]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines (IAE)
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain 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 proposed AD was prompted by
corrosion found on the HPC front hub. This proposed AD would require
replacing the HPC front hub with a part eligible for installation. We
are proposing this AD to address the unsafe condition on these
products.
DATES: We must receive comments on this proposed AD by August 13, 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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
[[Page 30371]]
For service information identified in this NPRM, contact
International Aero Engines (IAE), 400 Main Street, East Hartford, CT
06118; phone: 800-565-0140; email: [email protected]; internet: http://fleetcare.pw.utc.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.
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-
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 NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket
shortly after receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0431;
Product Identifier 2018-NE-16-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM 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 NPRM.
Discussion
We received 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.
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.
FAA's Determination
We are proposing 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.
Proposed AD Requirements
This proposed AD would require removing from service the HPC front
hub, P/N 30G2401, and replacing it with a part eligible for
installation.
Costs of Compliance
We estimate that this proposed AD affects 16 engines installed on
airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Replace HPC front hub................. 0 work-hours x $85 per $11,600 $11,600 $185,600
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
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The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
International Aero Engines: Docket No. FAA-2018-0431; Product
Identifier 2018-NE-16-AD.
(a) Comments Due Date
We must receive comments by August 13, 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 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. 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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(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)(1) 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
(1) 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].
(2) For service information identified in this AD, contact
International Aero Engines (IAE), 400 Main Street, East Hartford, CT
06118; phone: 800-565-0140; email: [email protected]; internet:
http://fleetcare.pw.utc.com. You may view this referenced 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.
Issued in Burlington, MA, on June 22, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018-13795 Filed 6-27-18; 8:45 am]
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