[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]


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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; 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.

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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: http://fleetcare.pw.utc.com. You may view this service 
information at the FAA, Engine and Propeller Standards Branch, 1200

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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 http://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 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 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.
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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

    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:

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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(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]
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