Airworthiness Directives; Honeywell International Inc. Turbofan Engines, 46379-46382 [2017-21285]

Download as PDF Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations (f) When an appeal is required. Before seeking review by a court of a component’s adverse determination, a requester generally must first submit a timely administrative appeal. § 102.10 Preservation of records. Each component shall preserve all correspondence pertaining to the requests that it receives under this subpart, as well as copies of all requested records, until disposition or destruction is authorized pursuant to title 44 of the United States Code or the General Records Schedule 14 of the National Archives and Records Administration. Records shall not be disposed of or destroyed while they are the subject of a pending request, appeal, or lawsuit under the FOIA. § 102.11 Subpoenas. (a) The person to whom the subpoena is directed must consult with SBA counsel in the relevant SBA office, who will seek approval for compliance from the Associate General Counsel for Litigation. Except where the subpoena requires the testimony of an employee of the Inspector General’s office, or records within the possession of the Inspector General, the Associate General Counsel may delegate the authorization for appropriate production of documents or testimony to local SBA counsel. (b) If SBA counsel approves compliance with the subpoena, SBA will comply. (c) If SBA counsel disapproves compliance with the subpoena, SBA will not comply, and will base such noncompliance on an appropriate legal basis such as privilege or a statute. (d) SBA counsel must provide a copy of any subpoena relating to a criminal matter to SBA’s Inspector General prior to its return date. ethrower on DSK3G9T082PROD with RULES Appendix A to Subpart A of Part 102— Records Maintained by SBA I. Information Generally Exempt From Disclosure a. Non-statistical information on pending, declined, withdrawn, or canceled applications. b. Non-statistical information on defaults, delinquencies, losses etc. c. Loan status, other than charged-off or paid-in-full. d. Home disaster loan status and interest rate. e. Financial statements, credit reports, business plans, plant lay-outs, marketing strategy, advertising plans, fiscal projections, pricing information, payroll information, private sector experience and contracts, IRS forms, purchase information, banking information, corporate structure, research plans and client list of applicant/recipient. VerDate Sep<11>2014 16:56 Oct 04, 2017 Jkt 244001 f. Portions of: Certificate of Competency records, Requests for Size Determinations, 8(a) Business Development Plans, loan applications, SBIC applications, loan officer’s reports. g. Internal documents not incorporated into final Agency action, pending internal recommendations on applications for assistance, SBA/attorney-client communications, pending litigation documents and investigatory documents. Discretionary disclosure policy must be utilized. h. Personal history and financial statements, tax forms, resumes, all nongovernment career experience, communications regarding applicant’s character, home addresses and telephone numbers, social security numbers, birth dates and medical records. Portions of Inspector General (IG) reports, audit reports, program investigation records and any other records which, if released, would interfere with the Government’s law enforcement proceedings and/or would reveal the identity of a confidential source and documents relating to pending litigation and investigations. Requests for IG documents must be referred to the Office of the Inspector General, Counsel Division. i. Financial information on portfolio companies. j. Information originating from other agencies should be referred to those agencies for disclosure determinations. II. Information Generally Disclosed a. Names and business addresses of recipients of approved loans, SBIC licenses, Certificates of Competency, lease guarantees, surety bond guarantees and requests for counseling. b. Names of officers, directors, stockholders or partners of recipient firms. c. Kinds and amounts of loans, loan terms, interest rates (except on home disaster loans), maturity dates, general purpose, etc. d. Statistical data on assistance, loans, defaults, contracts, counseling, etc. e. Decisions, rulings and records showing final Agency actions in specific factual situations if identifying details exempt from disclosure are first deleted. f. Awarded contracts: names, amounts, dates, contracting agencies. g. Identity of participating banks. h. List of 8(a) participants, date of entry, FPPT dates and NAICS codes. i. OHA opinions and decisions. j. Names of SBA employees, grades, titles, and duty stations. Linda E. McMahon, Administrator. [FR Doc. 2017–21204 Filed 10–4–17; 8:45 am] BILLING CODE 8025–01–P PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 46379 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0034; Product Identifier 2016–NE–32–AD; Amendment 39– 19063; AD 2017–20–06] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. (Honeywell) AS907–1–1A turbofan engines. This AD was prompted by reports of loss of power due to failure of the second stage low-pressure turbine (LPT2) blade. This AD requires a onetime inspection of the LPT2 blades and, if the blades fail the inspection, the replacement of the blades with a part eligible for installation. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 9, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 9, 2017. ADDRESSES: For service information identified in this final rule, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034–2802; phone: 800–601–3099; Internet: https:// myaerospace.honeywell.com/wps/ portal. 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– 7125. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0034. SUMMARY: 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–2017– 0034; or in person at the Docket Management Facility 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 the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. E:\FR\FM\05OCR1.SGM 05OCR1 46380 Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations 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: Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562– 627–5210; email: joseph.costa@faa.gov. SUPPLEMENTARY INFORMATION: eligible for installation. We are issuing this AD to prevent failure of the LPT2 blades, failure of one or more engines, and loss of the airplane. Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Honeywell International Inc. (Honeywell) AS907– 1–1A turbofan engines. The NPRM published in the Federal Register on June 20, 2017 (82 FR 28028). The NPRM was prompted by reports of loss of power due to failure of the second stage LPT2 blade from high-cycle fatigue in the blade’s dovetail region. The NPRM proposed to require a one-time inspection of the LPT2 blades and, if the blades fail the inspection, the replacement of the blades with a part We reviewed the relevant data 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 correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Comments We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion Related Service Information Under 1 CFR Part 51 We reviewed Honeywell Service Bulletin (SB) AS907–72–9067, Revision 1, dated March 20, 2017. This SB describes procedures for inspecting the LPT2 blades. 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. Other Related Service Information We reviewed Honeywell SB AS907– 72–9067, Revision 0, dated December 12, 2016, which also describes procedures for inspecting the LPT2 blades. We also reviewed the Honeywell Light Maintenance Manual, AS907–1– 1A, 72–00–00, Section 72–05–12, dated May 25, 2016, and Section 72–55–03, dated September 27, 2011, which provide additional guidance for performing borescope inspections. Costs of Compliance We estimate that this AD affects 40 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Borescope inspection ...................................... Report results of inspection ............................ 10 work-hours × $85 per hour = $850 ........... 1 work-hour × $85 per hour = $85 ................. We estimate the following costs to do any necessary replacements that would be required based on the results of the Cost per product Parts cost $0 0 $850 85 Cost on U.S. operators $34,000 3,400 inspection. We estimate that 40 engines will need this replacement. ON-CONDITION COSTS Action Labor cost Replacement of the LPT2 blade set ............................ 50 work-hours × $85 per hour = $4,250 ...................... ethrower on DSK3G9T082PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and VerDate Sep<11>2014 16:56 Oct 04, 2017 Jkt 244001 reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave., SW., Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. 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 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Parts cost $50,000 Cost per product $54,250 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. E:\FR\FM\05OCR1.SGM 05OCR1 Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations 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 to the extent that it justifies making a regulatory distinction, 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): ethrower on DSK3G9T082PROD with RULES ■ 2017–20–06 Honeywell International Inc.: Amendment 39–19063; Docket No. FAA–2017–0034; Product Identifier 2016–NE–32–AD. (a) Effective Date This AD is effective November 9, 2017. VerDate Sep<11>2014 16:56 Oct 04, 2017 Jkt 244001 (b) Affected ADs None. (c) Applicability This AD applies to Honeywell International Inc. (Honeywell) AS907–1–1A turbofan engines with second stage lowpressure turbine (LPT2) rotor blades, part number (P/N) 3035602–1, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by reports of loss of power due to failure of the LPT2 blade. We are issuing this AD to prevent failure of the LPT2 blades, failure of one or more engines, and loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For LPT2 rotor blades, P/N 3035602–1 that have more than 8,000 hours since new on the effective date of this AD, perform a one-time borescope inspection for wear of the Z gap contact area at the blade tip shroud for each of the 62 LPT2 rotor blades within 200 hours time in service after the effective date of this AD. (2) Use the Accomplishment Instructions, Paragraph 3.B.(1), of Honeywell Service Bulletin (SB) AS907–72–9067, Revision 1, dated March 20, 2017, to do the inspection. (3) If the measured wear and/or fretting of any Z gap contact area is greater than 0.005 inch, replace the LPT2 rotor assembly with a part eligible for installation before further flight. (4) Do the following actions within 200 hours time in service after the effective date of this AD: (i) Using a borescope make a clear digital image of the Z gap contact area at the blade tip shroud of the 62 LPT2 rotor blades. (ii) Identify the three Z gap contact areas with the greatest amount of wear and/or fretting. (iii) Record the blade position on the LPT2 rotor assembly and the measured wear of the three Z gap contact areas with the greatest amount of wear and/or fretting. (iv) Send the results to Honeywell at engine.reliability@honeywell.com within 30 days after completing these actions. (g) Credit for Previous Actions You may take credit for the actions required by paragraphs (f)(1) and (4) of this AD, if you performed these actions before the effective date of this AD using Honeywell SB AS907–72–9067, Revision 0, dated December 12, 2016. (h) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 46381 Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, may 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 Los Angeles ACO Branch, send it to the attention of the person identified in paragraph (j) of this AD. (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 Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562–627– 5210; email: joseph.costa@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) Honeywell Service Bulletin AS907–72– 9067, Revision 1, dated March 20, 2017. (ii) Reserved. (3) For Honeywell service information identified in this AD, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034–2802; phone: 800–601–3099; Internet: https://myaerospace. honeywell.com/wps/portal. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. E:\FR\FM\05OCR1.SGM 05OCR1 46382 Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations Issued in Burlington, Massachusetts, on September 22, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–21285 Filed 10–4–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9183; Product Identifier 2016–NM–059–AD; Amendment 39–19029; AD 2017–18–20] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 707 airplanes equipped with a main cargo door (MCD). This AD was prompted by analysis of the cam support assemblies of the MCD that indicated the repetitive high frequency eddy current (HFEC) inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the MCD could fail. This AD requires repetitive ultrasonic inspections for cracking of the cam support assemblies of the MCD, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 9, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 9, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016– 9183. ethrower on DSK3G9T082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:56 Oct 04, 2017 Jkt 244001 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–2016– 9183; or in person at the Docket Management Facility 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 the Docket Office (phone: 800–647–5527) is Docket Management Facility, 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: Chandra Ramdoss, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5239; fax: 562–627– 5210; email: chandraduth.ramdoss@ 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 all The Boeing Company Model 707 airplanes. The NPRM published in the Federal Register on October 4, 2016 (81 FR 68376) (‘‘the NPRM’’). The NPRM was prompted by analysis of the cam support assemblies of the MCD that indicated the repetitive HFEC inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the MCD could fail. The NPRM proposed to require repetitive ultrasonic inspections for cracking of the cam support assemblies of the MCD, and replacement if necessary. We are issuing this AD to detect and correct cracking of the cam support assemblies of the MCD. Such cracking could result in reduced structural integrity of the MCD and consequent rapid decompression of the airplane. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Revise Applicability Boeing stated that Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, affects only Boeing factory and Boeing-converted freighters, but the PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 proposed AD extends the applicability to all Model 707 airplanes, including the ones that have been converted by non-Boeing supplemental type certificates (STCs). We infer the commenter is requesting that the actions of the service information only be required for Model 707 airplanes identified in the Effectivity paragraph of Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. We agree that the applicability of the proposed AD should not include Model 707 airplanes that do not have an MCD. However, we disagree that the AD applicability should be limited to the airplanes identified in the Effectivity paragraph of Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, which only identifies Boeing factory and Boeing-converted freighters. The cam support assemblies having the affected part number could be installed at original aircraft manufacture, or during passenger-tofreighter modification. We expect that the actions specified in Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016, can be accomplished on airplanes that are not identified in that service information. However, if an operator with a Model 707 freighter that is not a part of Boeing type design cannot accomplish the required actions in the service information, or prefers to use different service information that is specific to their design, approval of an alternative method of compliance (AMOC) can be requested in accordance with paragraph (j) of this AD. We revised this AD to limit the applicability to Model 707 airplanes equipped with an MCD. Request To Supersede AD 80–08–10 R1, Amendment 39–3830 (45 FR 46343, July 10, 1980) (‘‘AD 80–08–10 R1’’) Boeing requested that we revise the NPRM to supersede AD 80–08–10 R1. Boeing stated that AD 80–08–10 R1 mandates HFEC inspections of MCD cam support assemblies having part numbers (P/Ns) 69–23588–1 and 69– 23588–2, as specified in Boeing Service Bulletin 707–A3387. Boeing explained that the NPRM is adding cam support assemblies having P/Ns 69–23588–1 and 69–23588–2 to the list in Boeing 707 Alert Service Bulletin A3542, dated February 12, 2016. Boeing asserted that the addition of these components to the list of affected parts would mean that the operators have to perform HFEC inspections of cam support assemblies having P/Ns 69–23588–1 and 69– 23588–2, as specified in AD 80–08–10 R1, and perform ultrasonic inspections of the same components, as specified in the proposed AD. Boeing explained that E:\FR\FM\05OCR1.SGM 05OCR1

Agencies

[Federal Register Volume 82, Number 192 (Thursday, October 5, 2017)]
[Rules and Regulations]
[Pages 46379-46382]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-21285]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0034; Product Identifier 2016-NE-32-AD; Amendment 
39-19063; AD 2017-20-06]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Honeywell International Inc. (Honeywell) AS907-1-1A turbofan engines. 
This AD was prompted by reports of loss of power due to failure of the 
second stage low-pressure turbine (LPT2) blade. This AD requires a one-
time inspection of the LPT2 blades and, if the blades fail the 
inspection, the replacement of the blades with a part eligible for 
installation. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective November 9, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 9, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 
85034-2802; phone: 800-601-3099; Internet: https://myaerospace.honeywell.com/wps/portal. 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) 238-7125. It is 
also available on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-0034.

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-2017-
0034; or in person at the Docket Management Facility 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 the Docket Office 
(phone: 800-647-5527) is Document Management Facility, U.S.

[[Page 46380]]

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: Joseph Costa, Aerospace Engineer, Los 
Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; 
phone: 562-627-5246; fax: 562-627-5210; email: joseph.costa@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 certain Honeywell 
International Inc. (Honeywell) AS907-1-1A turbofan engines. The NPRM 
published in the Federal Register on June 20, 2017 (82 FR 28028). The 
NPRM was prompted by reports of loss of power due to failure of the 
second stage LPT2 blade from high-cycle fatigue in the blade's dovetail 
region. The NPRM proposed to require a one-time inspection of the LPT2 
blades and, if the blades fail the inspection, the replacement of the 
blades with a part eligible for installation. We are issuing this AD to 
prevent failure of the LPT2 blades, failure of one or more engines, and 
loss of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data 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 correcting 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 Honeywell Service Bulletin (SB) AS907-72-9067, Revision 
1, dated March 20, 2017. This SB describes procedures for inspecting 
the LPT2 blades. 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.

Other Related Service Information

    We reviewed Honeywell SB AS907-72-9067, Revision 0, dated December 
12, 2016, which also describes procedures for inspecting the LPT2 
blades. We also reviewed the Honeywell Light Maintenance Manual, AS907-
1-1A, 72-00-00, Section 72-05-12, dated May 25, 2016, and Section 72-
55-03, dated September 27, 2011, which provide additional guidance for 
performing borescope inspections.

Costs of Compliance

    We estimate that this AD affects 40 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
----------------------------------------------------------------------------------------------------------------
Borescope inspection..................  10 work-hours x $85 per               $0            $850         $34,000
                                         hour = $850.
Report results of inspection..........  1 work-hour x $85 per                  0              85           3,400
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We 
estimate that 40 engines will need this replacement.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                       Cost per
                 Action                          Labor cost           Parts cost        product
--------------------------------------------------------------------------------------------------
Replacement of the LPT2 blade set......  50 work-hours x $85 per           $50,000         $54,250
                                          hour = $4,250.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave., SW., Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

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.

[[Page 46381]]

    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 to the extent 
that it justifies making a regulatory distinction, 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 adding the following new airworthiness 
directive (AD):

2017-20-06 Honeywell International Inc.: Amendment 39-19063; Docket 
No. FAA-2017-0034; Product Identifier 2016-NE-32-AD.

(a) Effective Date

    This AD is effective November 9, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
AS907-1-1A turbofan engines with second stage low-pressure turbine 
(LPT2) rotor blades, part number (P/N) 3035602-1, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by reports of loss of power due to failure 
of the LPT2 blade. We are issuing this AD to prevent failure of the 
LPT2 blades, failure of one or more engines, and loss of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) For LPT2 rotor blades, P/N 3035602-1 that have more than 
8,000 hours since new on the effective date of this AD, perform a 
one-time borescope inspection for wear of the Z gap contact area at 
the blade tip shroud for each of the 62 LPT2 rotor blades within 200 
hours time in service after the effective date of this AD.
    (2) Use the Accomplishment Instructions, Paragraph 3.B.(1), of 
Honeywell Service Bulletin (SB) AS907-72-9067, Revision 1, dated 
March 20, 2017, to do the inspection.
    (3) If the measured wear and/or fretting of any Z gap contact 
area is greater than 0.005 inch, replace the LPT2 rotor assembly 
with a part eligible for installation before further flight.
    (4) Do the following actions within 200 hours time in service 
after the effective date of this AD:
    (i) Using a borescope make a clear digital image of the Z gap 
contact area at the blade tip shroud of the 62 LPT2 rotor blades.
    (ii) Identify the three Z gap contact areas with the greatest 
amount of wear and/or fretting.
    (iii) Record the blade position on the LPT2 rotor assembly and 
the measured wear of the three Z gap contact areas with the greatest 
amount of wear and/or fretting.
    (iv) Send the results to Honeywell at 
engine.reliability@honeywell.com within 30 days after completing 
these actions.

(g) Credit for Previous Actions

    You may take credit for the actions required by paragraphs 
(f)(1) and (4) of this AD, if you performed these actions before the 
effective date of this AD using Honeywell SB AS907-72-9067, Revision 
0, dated December 12, 2016.

(h) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, may 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 
Los Angeles ACO Branch, send it to the attention of the person 
identified in paragraph (j) of this AD.
    (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 Joseph Costa, 
Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount 
Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-
5210; email: joseph.costa@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) Honeywell Service Bulletin AS907-72-9067, Revision 1, dated 
March 20, 2017.
    (ii) Reserved.
    (3) For Honeywell service information identified in this AD, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 
85034-2802; phone: 800-601-3099; Internet: https://myaerospace.honeywell.com/wps/portal.
    (4) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 
For information on the availability of this material at the FAA, 
call 781-238-7125.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


[[Page 46382]]


    Issued in Burlington, Massachusetts, on September 22, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-21285 Filed 10-4-17; 8:45 am]
 BILLING CODE 4910-13-P