2018-24250. 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: [phone]; email: [e-mail]; 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. 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: [phone]) 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: [phone]; fax: [phone]; email: [e-mail].

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	Parts cost	Cost per product	Cost on U.S. operators
Replace HPC front hub	0 work-hours × $85 per hour = $85	$11,600	$11,600	$185,600

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

(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

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13

[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.

(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.

(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: [e-mail].

(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: [phone]; fax: [phone]; email: [e-mail].

(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.