Airworthiness Directives; Airbus Helicopters, 39506-39509 [2017-17084]

Download as PDF 39506 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations that a violation of Loan Program Requirements constitutes default under their respective agreements with SBA. (1) Additional agreements by CDCs. By obtaining approval for 504 loans after October 20, 2017, a CDC consents to the remedies in § 120.1500(e)(3) and waives in advance any right it may have to contest the validity of the appointment of a receiver. The CDC agrees that its consent to SBA’s application to a Federal court of competent jurisdiction for appointment of a receiver of SBA’s choosing, an injunction or other equitable relief, and the CDC’s consent in advance to the court’s granting of SBA’s application, may be enforced upon any basis in law or equity recognized by the court. (2) Additional agreements by SBA Supervised Lenders (except Other Regulated SBLCs). By making SBA 7(a) guaranteed loans after October 20, 2017, an SBA Supervised Lender (except an Other Regulated SBLC) consents to the remedies in § 120.1500(c)(3) and waives in advance any right it may have to contest the validity of the appointment of a receiver. The SBA Supervised Lender agrees that its consent to SBA’s application to a Federal court of competent jurisdiction for appointment of a receiver of SBA’s choosing, an injunction or other equitable relief, and the SBA Supervised Lender’s consent in advance to the court’s granting of SBA’s application, may be enforced upon any basis in law or equity recognized by the court. * * * * * ■ 47. Amend § 120.1500 by revising paragraph (c)(3) and adding paragraph (e)(3) to read as follows: § 120.1500 Types of enforcement actions—SBA Lenders. sradovich on DSK3GMQ082PROD with RULES * * * * * (c) * * * (3) Initiate request for appointment of receiver and/or other relief. The SBA may make application to any Federal court of competent jurisdiction for the court to take exclusive jurisdiction, without notice, of an SBA Supervised Lender, and SBA shall be entitled to the appointment of a receiver of SBA’s choosing to hold, administer, operate, and/or liquidate the SBA Supervised Lender; and to such injunctive or other equitable relief as may be appropriate. Without limiting the foregoing and with SBA’s written consent, the receiver may take possession of the portfolio of 7(a) loans and sell such loans to a third party, and/or take possession of servicing activities of 7(a) loans and sell such servicing rights to a third party. * * * * * VerDate Sep<11>2014 16:12 Aug 18, 2017 Jkt 241001 (e) * * * (3) Apply to any Federal court of competent jurisdiction for the court to take exclusive jurisdiction, without notice, of the CDC, and SBA shall be entitled to the appointment of a receiver of SBA’s choosing to hold, administer, operate and/or liquidate the CDC; and to such injunctive or other equitable relief as may be appropriate. Without limiting the foregoing and with SBA’s consent, the receiver may take possession of the portfolio of 504 loans and/or pending 504 loan applications, including for the purpose of carrying out an enforcement order under paragraph (e)(1) of this section. ■ 48. Amend § 120.1600 by: ■ a. Revising paragraph (a) introductory text; ■ b. Adding paragraph (a)(6); and ■ c. Revising paragraph (b)(4). The revisions and addition read as follows: § 120.1600 General procedures for enforcement actions against SBA Lenders, SBA Supervised Lenders, Other Regulated SBLCs, Management Officials, Other Persons, Intermediaries, and NTAPs. (a) In general. Except as otherwise set forth for the enforcement actions listed in paragraphs (a)(6), (b) and (c) of this section, SBA will follow the procedures listed below. * * * * * (6) Receiverships of Certified Development Companies and/or other relief. If SBA undertakes the appointment of a receiver for a Certified Development Company and/or injunctive or other equitable relief, paragraphs (a)(1) through (5) of this section will not apply and SBA will follow the applicable procedures under Federal law to obtain such remedies and to enforce the Certified Development Company’s consent and waiver in advance to those remedies. (b) * * * (4) Receiverships, transfer of assets and servicing activities. If SBA undertakes the appointment of a receiver for, or the transfer of assets or servicing rights of an SBA Supervised Lender and/or injunctive or other equitable relief, SBA will follow the applicable procedures under Federal law to obtain such remedies and to enforce the SBA Supervised Lender’s consent and waiver in advance to those remedies. * * * * * ■ 49. Amend § 120.1703 by revising paragraph (a)(4) to read as follows: § 120.1703 Qualifications to be a Pool Originator. (a) * * * PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 (4) Is in good standing with SBA (as the SBA determines), and is Satisfactory with the Office of the Comptroller of the Currency (OCC) if it is a national bank, the Federal Deposit Insurance Corporation if it is a bank not regulated by the OCC, the Financial Institutions Regulatory Authority if it is a member, the National Credit Union Administration if it is a credit union, as determined by SBA; and * * * * * ■ 50. Amend § 120.1707 by revising the fifth sentence and adding a sixth sentence to read as follows: § 120.1707 Seller’s retained Loan Interest. * * * In addition, in order to complete such sale, Seller must have the purchaser of its rights to the Pool Loan execute an allonge to the Seller’s First Lien Position 504 Loan Pool Guarantee Agreement in a form acceptable to SBA, acknowledging and accepting all terms of the Seller’s First Lien Position 504 Loan Pool Guarantee Agreement, and deliver the executed original allonge and a copy of the corresponding First Lien Position 504 Loan Pool Guarantee Agreement to the CSA. All Pool Loan payments related to a Seller Receipt and Servicing Retention Amount proposed for sale will be withheld by the CSA pending SBA acknowledgement of receipt of all executed documents required to complete the transfer. Subpart K—[Removed] 51. Remove Subpart K, consisting of §§ 120.1800 through 120.1900. ■ Dated: August 11, 2017. Linda E. McMahon, Administrator. [FR Doc. 2017–17447 Filed 8–18–17; 8:45 am] BILLING CODE 8025–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0419; Product Identifier 2015–SW–077–AD; Amendment 39–18991; AD 2017–17–01] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters (Airbus) Model AS332L2 SUMMARY: E:\FR\FM\21AUR1.SGM 21AUR1 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations sradovich on DSK3GMQ082PROD with RULES and EC225LP helicopters. This AD requires inspections of the main rotor (M/R) blade attachment pins (attachment pins). This AD was prompted by a report of three cracked attachment pins. The actions of this AD are intended to detect and prevent an unsafe condition on these products. DATES: This AD is effective September 25, 2017. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of September 25, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.helicopters.airbus.com/Website/ en/ref/Technical-Support_73.html. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0419. 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– 0419; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5116; email david.hatfield@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On May 11, 2017, at 82 FR 21956, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to VerDate Sep<11>2014 16:12 Aug 18, 2017 Jkt 241001 Airbus Model AS332L2 helicopters with an attachment pin part number (P/N) 332A31–2123–00 or P/N 332A31–2115– 20 installed and Model EC225LP helicopters with an attachment pin P/N 332A31–3204–20 installed. The NPRM proposed to require an initial and recurring inspection of each attachment pin for corrosion, a crack, and any pitting. If there is a crack or any pitting, the NPRM proposed to require replacing the attachment pin. If there is corrosion, the NPRM proposed to require removing the corrosion up to a maximum of four times. The NPRM also proposed to require performing these inspections prior to installing an attachment pin. The proposed requirements were intended to detect corrosion or a crack in an attachment pin and prevent loss of an M/R blade and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2015–0016, dated January 30, 2015, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Model AS 332 L2 and EC 225 LP helicopters with certain part-numbered attachment pins installed. EASA advises of three cracked attachment pins on a Model AS 332 L2 helicopter, which resulted from a combination of factors including corrosion that had initiated in the inner diameter area of the attachment pin chamfer. EASA states that if this condition is not detected and corrected, it may lead to failure of the attachment pin with loss of control of the helicopter. Due to design similarity, Model EC225LP helicopters are also affected by this issue. For these reasons, EASA AD No. 2015–0016 requires repetitive inspections of the attachment pins for corrosion. 39507 and the public interest require adopting the AD requirements as proposed. Differences Between This AD and the EASA AD The EASA AD does not require an inspection of the protective coating of each attachment pin for Model EC225LP helicopters. This AD requires inspecting the protective coating of each attachment pin for both model helicopters. The EASA AD requires ensuring there are no corrosion pits without a corresponding corrective action. This AD requires replacing an attachment pin that has any pitting. The EASA AD requires a non-destructive inspection if in doubt about whether there is a crack, while this AD does not. Lastly, the EASA AD requires contacting and returning to Airbus Helicopters any attachment pin with a crack, and this AD does not. FAA’s Determination Related Service Information Under 1 CFR Part 51 We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. AS332– 05.00.99, Revision 0, dated December 22, 2014 (AS332–05.00.99), for Model AS332L2 helicopters and Airbus Helicopters ASB No. EC225–05A040, Revision 0, dated December 22, 2014 (EC225–05A040), for Model EC225LP helicopters. Airbus Helicopters advises of cracks discovered in attachment pins that resulted from a combination of factors, but mainly corrosion which initiated in the inner diameter at the chamfer. This service information specifies repetitively inspecting for corrosion and cracks and ensuring there are no corrosion pits in the attachment pins. If there is corrosion, this service information allows an attachment pin to be reworked up to four times before removing it from service. If there is a crack, this service information specifies contacting and sending the attachment pin to Airbus Helicopters. 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. These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety Costs of Compliance We estimate that this AD affects 5 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour. For Model AS332L2 helicopters, there are no costs of compliance with this AD because there are no helicopters with this type certificate on the U.S. Registry. For Model EC225LP helicopters, which have ten attachment pins Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\21AUR1.SGM 21AUR1 39508 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations installed, inspecting the attachment pins takes about 1 work-hour for a total cost of $85 per helicopter and $425 for the U.S. fleet. Removing corrosion takes about 1 work-hour for a total cost of $85 per attachment pin. Replacing an attachment pin takes negligible additional labor time and required parts would cost about $5,720. 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 helicopters identified in this rulemaking action. sradovich on DSK3GMQ082PROD with RULES 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 16:12 Aug 18, 2017 Jkt 241001 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority for This Rulemaking VerDate Sep<11>2014 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–17–01 Airbus Helicopters: Amendment 39–18991; Docket No. FAA–2017–0419; Product Identifier 2015–SW–077–AD. (a) Applicability This AD applies to the following helicopters, certificated in any category: (1) Model AS332L2 helicopters with a main rotor (M/R) blade attachment pin (attachment pin) part number (P/N) 332A31– 2123–00 or P/N 332A31–2115–20 installed; and (2) Model EC225LP helicopters with an attachment pin P/N 332A31–3204–20 installed. (b) Unsafe Condition This AD defines the unsafe condition as corrosion or a crack in an attachment pin. This condition could result in loss of an M/ R blade and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective September 25, 2017. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) For Model AS332L2 helicopters, within 410 hours time-in-service (TIS), and for Model EC225LP helicopters within 660 hours TIS, remove each attachment pin and inspect the protective coating on the inside of the attachment pin for scratches and missing protective coating. (i) If there is a scratch or any missing protective coating, sand the attachment pin to remove the varnish in the area depicted as ‘‘Area A’’ in Figure 1 of Airbus Helicopters Alert Service Bulletin (ASB) No. AS332– 05.00.99, Revision 0, dated December 22, 2014 (AS332–05.00.99), or Airbus Helicopters ASB No. EC225–05A040, Revision 0, dated December 22, 2014 (EC225–05A040), as applicable to your model helicopter. (ii) Using a 10X or higher power magnifying glass, inspect for corrosion and pitting at the chamfer. An example of pitting is shown in the Accomplishment PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Instructions, paragraph 3.B.3., Note 1, of AS332–05.00.99, and paragraph 3.B.2., Note 1, of EC225–05A040. If there is any corrosion, remove the corrosion. If there is any pitting, replace the attachment pin. Do not sand the attachment pin to remove a corrosion pit. (iii) Using a 10X or higher power magnifying glass, inspect the inside and outside of the attachment pin for a crack in the areas depicted as ‘‘Area A’’ and ‘‘Area B’’ in Figure 1 of AS332–05.00.99 or EC225– 05A040, as applicable to your model helicopter. Pay particular attention to the chamfer in ‘‘Area A.’’ If there is a crack, remove the attachment pin from service. (2) Thereafter, for Model AS332L2 helicopters, at intervals not to exceed 825 hours TIS or 26 months, whichever occurs first; and for Model EC225LP helicopters, at intervals not to exceed 1,320 hours TIS or 26 months, whichever occurs first; perform the actions specified in paragraph (e)(1) of this AD. Corrosion may be removed from an attachment pin as specified in paragraph (e)(1)(ii) of this AD a maximum of four times. If there is a fifth occurrence of corrosion on an attachment pin, before further flight, remove the attachment pin from service. (3) Do not install an attachment pin P/N 332A31–2123–00, P/N 332A31–2115–20, or P/N 332A31–3204–20 on any helicopter unless you have complied with the actions in paragraph (e)(1) of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5116; email 9– ASW–FTW–AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) No. 2015–0016, dated January 30, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2017–0419. (h) Subject Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor System. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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. E:\FR\FM\21AUR1.SGM 21AUR1 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations (i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS332–05.00.99, Revision 0, dated December 22, 2014. (ii) Airbus Helicopters ASB No. EC225– 05A040, Revision 0, dated December 22, 2014. (3) For Airbus Helicopters service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641– 3775; or at http:// www.helicopters.airbus.com/Website/en/ref/ Technical-Support_73.html. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (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. Issued in Fort Worth, Texas, on August 7, 2017. Scott A. Horn, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2017–17084 Filed 8–18–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0335; Product Identifier 2017–NM–025–AD; Amendment 39–18994; AD 2017–17–04] 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 all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This AD was prompted by a report of cracks in the upper aft skin of the right wing at certain fastener holes along the rear spar upper chord. This AD requires repetitive inspections for cracking of the upper aft skin of the wings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 25, 2017. The Director of the Federal Register approved the incorporation by reference sradovich on DSK3GMQ082PROD with RULES 16:12 Aug 18, 2017 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– 0335; 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: Payman Soltani, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5313; fax: 562–627– 5210; email: payman.soltani@faa.gov. SUPPLEMENTARY INFORMATION: Discussion SUMMARY: VerDate Sep<11>2014 of a certain publication listed in this AD as of September 25, 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; 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–2017– 0335. Jkt 241001 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. The NPRM published in the Federal Register on May 17, 2017 (82 FR 22619) (‘‘the NPRM’’). The NPRM was prompted by a report of cracks in the upper aft skin of the right wing at certain fastener holes along the rear spar upper chord. The NPRM proposed to require repetitive inspections for cracking of the upper aft skin of the wings, and repair if necessary. Comments We gave the public the opportunity to participate in developing this AD. The PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 39509 following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM Boeing and Robert Simpson concurred with the content of the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC) ST01219SE does not affect compliance with the actions specified in the NPRM. We agree with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the change described previously and 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737–57A1332, dated January 3, 2017. This service information describes procedures for repetitive detailed inspections of the upper aft skin of the wings for cracking. 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. Costs of Compliance We estimate that this AD affects 471 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\21AUR1.SGM 21AUR1

Agencies

[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39506-39509]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17084]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0419; Product Identifier 2015-SW-077-AD; Amendment 
39-18991; AD 2017-17-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters (Airbus) Model AS332L2

[[Page 39507]]

and EC225LP helicopters. This AD requires inspections of the main rotor 
(M/R) blade attachment pins (attachment pins). This AD was prompted by 
a report of three cracked attachment pins. The actions of this AD are 
intended to detect and prevent an unsafe condition on these products.

DATES: This AD is effective September 25, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of September 25, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.helicopters.airbus.com/Website/en/ref/Technical-Support_73.html. You may review the referenced service information at 
the FAA, Office of the Regional Counsel, Southwest Region, 10101 
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. It is also available 
on the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2017-0419.

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-
0419; or in person at the Docket Operations Office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the European Aviation Safety Agency (EASA) AD, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
the Docket Operations Office (phone: 800-647-5527) is U.S. Department 
of Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5116; 
email david.hatfield@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On May 11, 2017, at 82 FR 21956, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 by adding an AD that would apply to Airbus Model AS332L2 
helicopters with an attachment pin part number (P/N) 332A31-2123-00 or 
P/N 332A31-2115-20 installed and Model EC225LP helicopters with an 
attachment pin P/N 332A31-3204-20 installed. The NPRM proposed to 
require an initial and recurring inspection of each attachment pin for 
corrosion, a crack, and any pitting. If there is a crack or any 
pitting, the NPRM proposed to require replacing the attachment pin. If 
there is corrosion, the NPRM proposed to require removing the corrosion 
up to a maximum of four times. The NPRM also proposed to require 
performing these inspections prior to installing an attachment pin. The 
proposed requirements were intended to detect corrosion or a crack in 
an attachment pin and prevent loss of an M/R blade and subsequent loss 
of control of the helicopter.
    The NPRM was prompted by AD No. 2015-0016, dated January 30, 2015, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, to correct an unsafe condition for Airbus Model AS 
332 L2 and EC 225 LP helicopters with certain part-numbered attachment 
pins installed. EASA advises of three cracked attachment pins on a 
Model AS 332 L2 helicopter, which resulted from a combination of 
factors including corrosion that had initiated in the inner diameter 
area of the attachment pin chamfer. EASA states that if this condition 
is not detected and corrected, it may lead to failure of the attachment 
pin with loss of control of the helicopter. Due to design similarity, 
Model EC225LP helicopters are also affected by this issue.
    For these reasons, EASA AD No. 2015-0016 requires repetitive 
inspections of the attachment pins for corrosion.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are issuing this AD because we evaluated all information 
provided by EASA and determined the unsafe condition exists and is 
likely to exist or develop on other helicopters of these same type 
designs and that air safety and the public interest require adopting 
the AD requirements as proposed.

Differences Between This AD and the EASA AD

    The EASA AD does not require an inspection of the protective 
coating of each attachment pin for Model EC225LP helicopters. This AD 
requires inspecting the protective coating of each attachment pin for 
both model helicopters. The EASA AD requires ensuring there are no 
corrosion pits without a corresponding corrective action. This AD 
requires replacing an attachment pin that has any pitting. The EASA AD 
requires a non-destructive inspection if in doubt about whether there 
is a crack, while this AD does not. Lastly, the EASA AD requires 
contacting and returning to Airbus Helicopters any attachment pin with 
a crack, and this AD does not.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. 
AS332-05.00.99, Revision 0, dated December 22, 2014 (AS332-05.00.99), 
for Model AS332L2 helicopters and Airbus Helicopters ASB No. EC225-
05A040, Revision 0, dated December 22, 2014 (EC225-05A040), for Model 
EC225LP helicopters. Airbus Helicopters advises of cracks discovered in 
attachment pins that resulted from a combination of factors, but mainly 
corrosion which initiated in the inner diameter at the chamfer. This 
service information specifies repetitively inspecting for corrosion and 
cracks and ensuring there are no corrosion pits in the attachment pins. 
If there is corrosion, this service information allows an attachment 
pin to be reworked up to four times before removing it from service. If 
there is a crack, this service information specifies contacting and 
sending the attachment pin to Airbus Helicopters.
    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.

Costs of Compliance

    We estimate that this AD affects 5 helicopters of U.S. Registry. We 
estimate that operators may incur the following costs in order to 
comply with this AD. Labor costs are estimated at $85 per work-hour.
    For Model AS332L2 helicopters, there are no costs of compliance 
with this AD because there are no helicopters with this type 
certificate on the U.S. Registry.
    For Model EC225LP helicopters, which have ten attachment pins

[[Page 39508]]

installed, inspecting the attachment pins takes about 1 work-hour for a 
total cost of $85 per helicopter and $425 for the U.S. fleet. Removing 
corrosion takes about 1 work-hour for a total cost of $85 per 
attachment pin. Replacing an attachment pin takes negligible additional 
labor time and required parts would cost about $5,720.

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 helicopters identified in this 
rulemaking action.

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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

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):

2017-17-01 Airbus Helicopters: Amendment 39-18991; Docket No. FAA-
2017-0419; Product Identifier 2015-SW-077-AD.

(a) Applicability

    This AD applies to the following helicopters, certificated in 
any category:
    (1) Model AS332L2 helicopters with a main rotor (M/R) blade 
attachment pin (attachment pin) part number (P/N) 332A31-2123-00 or 
P/N 332A31-2115-20 installed; and
    (2) Model EC225LP helicopters with an attachment pin P/N 332A31-
3204-20 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as corrosion or a crack in 
an attachment pin. This condition could result in loss of an M/R 
blade and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective September 25, 2017.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) For Model AS332L2 helicopters, within 410 hours time-in-
service (TIS), and for Model EC225LP helicopters within 660 hours 
TIS, remove each attachment pin and inspect the protective coating 
on the inside of the attachment pin for scratches and missing 
protective coating.
    (i) If there is a scratch or any missing protective coating, 
sand the attachment pin to remove the varnish in the area depicted 
as ``Area A'' in Figure 1 of Airbus Helicopters Alert Service 
Bulletin (ASB) No. AS332-05.00.99, Revision 0, dated December 22, 
2014 (AS332-05.00.99), or Airbus Helicopters ASB No. EC225-05A040, 
Revision 0, dated December 22, 2014 (EC225-05A040), as applicable to 
your model helicopter.
    (ii) Using a 10X or higher power magnifying glass, inspect for 
corrosion and pitting at the chamfer. An example of pitting is shown 
in the Accomplishment Instructions, paragraph 3.B.3., Note 1, of 
AS332-05.00.99, and paragraph 3.B.2., Note 1, of EC225-05A040. If 
there is any corrosion, remove the corrosion. If there is any 
pitting, replace the attachment pin. Do not sand the attachment pin 
to remove a corrosion pit.
    (iii) Using a 10X or higher power magnifying glass, inspect the 
inside and outside of the attachment pin for a crack in the areas 
depicted as ``Area A'' and ``Area B'' in Figure 1 of AS332-05.00.99 
or EC225-05A040, as applicable to your model helicopter. Pay 
particular attention to the chamfer in ``Area A.'' If there is a 
crack, remove the attachment pin from service.
    (2) Thereafter, for Model AS332L2 helicopters, at intervals not 
to exceed 825 hours TIS or 26 months, whichever occurs first; and 
for Model EC225LP helicopters, at intervals not to exceed 1,320 
hours TIS or 26 months, whichever occurs first; perform the actions 
specified in paragraph (e)(1) of this AD. Corrosion may be removed 
from an attachment pin as specified in paragraph (e)(1)(ii) of this 
AD a maximum of four times. If there is a fifth occurrence of 
corrosion on an attachment pin, before further flight, remove the 
attachment pin from service.
    (3) Do not install an attachment pin P/N 332A31-2123-00, P/N 
332A31-2115-20, or P/N 332A31-3204-20 on any helicopter unless you 
have complied with the actions in paragraph (e)(1) of this AD.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, FAA, may approve 
AMOCs for this AD. Send your proposal to: David Hatfield, Aviation 
Safety Engineer, Safety Management Section, Rotorcraft Standards 
Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 
(817) 222-5116; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office, before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) No. 2015-0016, dated January 30, 2015. You may view 
the EASA AD on the Internet at http://www.regulations.gov in Docket 
No. FAA-2017-0419.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor 
System.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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.

[[Page 39509]]

    (i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-
05.00.99, Revision 0, dated December 22, 2014.
    (ii) Airbus Helicopters ASB No. EC225-05A040, Revision 0, dated 
December 22, 2014.
    (3) For Airbus Helicopters service information identified in 
this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at http://www.helicopters.airbus.com/Website/en/ref/Technical-Support_73.html.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (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.

    Issued in Fort Worth, Texas, on August 7, 2017.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2017-17084 Filed 8-18-17; 8:45 am]
 BILLING CODE 4910-13-P