Airworthiness Directives; Airbus Airplanes, 24027-24030 [2017-10285]

Download as PDF Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations (i) Exception to Service Information Specifications Although Boeing Alert Service Bulletin 737–53A1343, dated March 25, 2016, specifies to contact Boeing for repair instructions, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (j) AD Provisions for Part 26 Supplemental Inspections Table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1343, dated March 25, 2016, specifies post-modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an alternative method of compliance. (k) Terminating Action for Certain Requirements of AD 2015–16–08 Accomplishing the modification required by paragraph (g) of this AD terminates the inspections required by paragraphs (g) and (h) of AD 2015–16–08 for the modified area only. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 ACO, send it to the attention of the person identified in paragraph (m) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. (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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (i) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (m) Related Information For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5264; fax: 562–627–5210; email: jennifer.tsakoumakis@faa.gov. (n) 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) Boeing Alert Service Bulletin 737– 53A1343, dated March 25, 2016. (ii) Reserved. (3) For Boeing service information identified in this AD, 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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 Renton, Washington, on May 10, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10265 Filed 5–24–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 24027 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0084; Directorate Identifier 2014–NM–181–AD; Amendment 39–18879; AD 2017–10–05] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; and Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). This AD was prompted by reports indicating that on airplanes that received a certain repair following crack findings, cracks can re-initiate. This AD requires repetitive inspections of the center wing frame (FR) 40 lower outboard radius for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 29, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http:// www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 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–2015–0084. 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–2015– 0084; or in person at the Docket Management Facility between 9 a.m. E:\FR\FM\25MYR1.SGM 25MYR1 24028 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A300 series airplanes; and Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes (collectively called Model A300–600 series airplanes). The SNPRM published in the Federal Register on November 10, 2016 (81 FR 78944) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on February 13, 2015 (80 FR 7992) (‘‘the NPRM’’). The NPRM proposed to require repetitive inspections for cracking of the FR 40 forward fittings for airplanes previously repaired. The NPRM was prompted by reports indicating that, on airplanes that received a certain repair following crack findings, cracks can re-initiate. The SNPRM proposed to require repetitive rototest, ultrasonic, high frequency eddy current, special detailed, and liquid penetrant inspections, as applicable, of the center wing FR 40 lower outboard radius for cracking, and related investigative and corrective actions if necessary. The SNPRM also proposed to add airplanes to the applicability. We are issuing this AD to detect and correct cracking on the FR 40 forward fittings, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0232R1, dated December 16, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 series airplanes; and Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes (collectively called Model A300–600 series airplanes). The MCAI states: Cracks were found on the lower outboard radius of the centre wing frame 40 forward fitting on in-service aeroplanes. This condition, if not detected and corrected, could lead to reduced structural integrity of the aeroplane. To address this unsafe condition, Airbus issued several inspection Service Bulletins (SB) and repair instructions. Consequently, EASA issued AD 2009–0094, which was later superseded by EASA AD 2011–0163 [which corresponds to FAA AD 2012–25–06, Amendment 39–17287 (77 FR 75833, December 26, 2012) (‘‘AD 2012–25–06’’)] and [EASA] AD 2014–0199 [which corresponds to the FAA NPRM], to require repetitive inspections and corrective actions on the affected areas. Since those [EASA] ADs were issued, additional in-service findings induced Airbus to do a new fatigue analysis, using a detailed Finite Element Model study, which resulted in defining new inspection methods. Prompted by these results, Airbus issued SB A300–57–0261, SB A300–57–6117 and SB A300–57–9034 to introduce these inspections. These new inspection SBs supersede and render obsolete inspection SB A300–53–0268 and SB A300–57–6052 and the All Operators Transmissions (AOT) A300–53A0391, AOT A300–57A6111, AOT A300–53W002–14 and AOT A300–57W003– 14. For the reasons described above, EASA issued AD 2015–0232, superseding [Direction ´ ´ Generale de l’Aviation Civile] DGAC France AD 1998–038–010(B) R1 [which corresponds to FAA AD 98–25–07, Amendment 39–10933 (63 FR 68167, December 10, 1998) (‘‘AD 98– 25–07’’)] and [DGAC France] AD 2003– 189(B), and EASA AD 2011–0163 and [EASA] AD 2014–0199, to require the new inspections of the affected areas within new thresholds and intervals. This [EASA] AD is revised to clarify the compliance time(s), introducing a Note after paragraph (1), and to alleviate the reporting requirements of paragraph (3). Required actions include repetitive rototest, ultrasonic, high frequency eddy current, special detailed, and liquid penetrant inspections, as applicable, of the center wing FR 40 lower outboard radius for cracking, and related investigative and corrective actions if necessary. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0084. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM 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 AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR Part 51 We reviewed the following service information: • Airbus Service Bulletin A300–57– 6117, dated May 28, 2015. • Airbus Service Bulletin A300–57– 0261, dated June 11, 2015. The service information describes procedures for repetitive ultrasonic, rototest, high frequency eddy current, special detailed, and liquid penetrant inspections, and related investigative and corrective actions. These documents are distinct since they apply to different airplane models. 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 29 airplanes of U.S. registry. We estimate the following costs to comply with this AD. ESTIMATED COSTS Action Labor cost Cost per product Inspections ............. Up to 91 work-hours × $85 per hour = $7,735 per inspection cycle. 1 work-hour × $85 per hour = $85 ....... Up to $7,735 per inspection cycle ........ Up to $224,315 per inspection cycle. $85 ........................................................ $2,465. Reporting ............... VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM Cost on U.S. operators 25MYR1 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. 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. Regulatory Findings We determined that 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: VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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): ■ 2017–10–05 Airbus: Amendment 39–18879; Docket No. FAA–2015–0084; Directorate Identifier 2014–NM–181–AD. (a) Effective Date This AD is effective June 29, 2017. (b) Affected ADs This AD affects AD 98–25–07, Amendment 39–10933 (63 FR 68167, December 10, 1998) (‘‘AD 98–25–07’’); and AD 2012–25–06, Amendment 39–17287 (77 FR 75833, December 26, 2012) (‘‘AD 2012–25–06’’). (c) Applicability This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(5) of this AD, except airplanes on which Airbus Modification 10221 has been embodied in production. (1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes. (3) Model A300 B4–605R and B4–622R airplanes. (4) Model A300 F4–605R and F4–622R airplanes. (5) Model A300 C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 24029 (e) Reason This AD was prompted by reports of cracks on the lower outboard radius of the center wing frame (FR) 40 forward fitting. We are issuing this AD to detect and correct cracking on the FR 40 forward fittings, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Except as provided by paragraph (i)(1) of this AD, at the applicable times specified in paragraph 1.E.(2), ‘‘Compliance,’’ of Airbus Service Bulletin A300–57–0261, dated June 11, 2015; or Airbus Service Bulletin A300– 57–6117, dated May 28, 2015; accomplish rototest, ultrasonic, high frequency eddy current, special detailed, and liquid penetrant inspections, as applicable, of the center wing FR 40 lower outboard radius for cracking, and do all applicable related investigative actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–0261, dated June 11, 2015; or Airbus Service Bulletin A300– 57–6117, dated May 28, 2015; as applicable. Do all applicable related investigative actions before further flight. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E. (2), ‘‘Compliance,’’ of Airbus Service Bulletin A300–57–0261, dated June 11, 2015; or Airbus Service Bulletin A300– 57–6117, dated May 28, 2015. (h) Corrective Actions If, during any inspection required by paragraph (g) of this AD, any crack is found, before further flight, accomplish the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–0261, dated June 11, 2015; or Airbus Service Bulletin A300–57–6117, dated May 28, 2015; as applicable; except as required by paragraph (i)(2) of this AD. (i) Service Information Exception (1) Where the service information specified in paragraph (g) of this AD specifies a compliance time ‘‘from this service bulletin issuance date,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where the service information specified in paragraph (h) of this AD specifies to contact Airbus for certain conditions, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (j) No Terminating Action for This AD Accomplishing a corrective action required by paragraph (h) of this AD, or accomplishing a preventative action specified in Airbus Service Bulletin A300–57–0260 or A300–57– 6116, as applicable, does not terminate the repetitive inspections required by paragraph (g) of this AD. E:\FR\FM\25MYR1.SGM 25MYR1 24030 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations (k) Terminating Action for Certain Requirements of Other ADs (1) Accomplishing the actions required by paragraph (g) of this AD terminates the actions required by paragraphs (a) and (b) of AD 98–25–07. (2) Accomplishing the actions required by paragraph (g) of this AD terminates the actions required by paragraphs (i) and (j) of AD 2012–25–06. (l) Reporting Requirements Within 60 days after any inspection required by paragraph (g) of this AD, or within 60 days after the effective date of this AD, whichever occurs later, report any findings, positive or negative, to Airbus Service Bulletin Reporting Online Application on Airbus World (https:// w3.airbus.com/). (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: 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 VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0232R1, dated December 16, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0084. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) 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 this AD specifies otherwise. (i) Airbus Service Bulletin A300–57–0261, dated June 11, 2015. (ii) Airbus Service Bulletin A300–57–6117, dated May 28, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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 Renton, Washington, on May 2, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10285 Filed 5–24–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9550; Directorate Identifier 2016–CE–026–AD; Amendment 39–18894; AD 2017–10–20] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA–31, PA– 31–300, PA–31–325, and PA–31–350 airplanes. This AD was prompted by fatigue cracking in the fuselage station (FS) 332.00 bulkhead common to the horizontal stabilizer front spar attachment. This AD requires repetitive inspections to detect cracks in the bulkhead and any necessary repairs. This AD also provides an optional modification if no cracks are found that will greatly reduce the likelihood of the specified cracks. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 29, 2017. ADDRESSES: For service information identified in this final rule, contact Piper Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (877) 879–0275; fax: none; email: customer.service@ piper.com; Internet: www.piper.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9550. 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–2016– 9550; 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 AD, the regulatory Frm 00032 Fmt 4700 Sfmt 4700 E:\FR\FM\25MYR1.SGM 25MYR1

Agencies

[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24027-24030]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10285]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0084; Directorate Identifier 2014-NM-181-AD; 
Amendment 39-18879; AD 2017-10-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and 
F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). This AD was 
prompted by reports indicating that on airplanes that received a 
certain repair following crack findings, cracks can re-initiate. This 
AD requires repetitive inspections of the center wing frame (FR) 40 
lower outboard radius for cracking, and related investigative and 
corrective actions if necessary. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective June 29, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 29, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 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-2015-
0084.

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-2015-
0084; or in person at the Docket Management Facility between 9 a.m.

[[Page 24028]]

and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to certain Airbus 
Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). The SNPRM 
published in the Federal Register on November 10, 2016 (81 FR 78944) 
(``the SNPRM''). We preceded the SNPRM with a notice of proposed 
rulemaking (NPRM) that published in the Federal Register on February 
13, 2015 (80 FR 7992) (``the NPRM''). The NPRM proposed to require 
repetitive inspections for cracking of the FR 40 forward fittings for 
airplanes previously repaired. The NPRM was prompted by reports 
indicating that, on airplanes that received a certain repair following 
crack findings, cracks can re-initiate. The SNPRM proposed to require 
repetitive rototest, ultrasonic, high frequency eddy current, special 
detailed, and liquid penetrant inspections, as applicable, of the 
center wing FR 40 lower outboard radius for cracking, and related 
investigative and corrective actions if necessary. The SNPRM also 
proposed to add airplanes to the applicability. We are issuing this AD 
to detect and correct cracking on the FR 40 forward fittings, which 
could result in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0232R1, dated December 16, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R 
series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). The MCAI states:

    Cracks were found on the lower outboard radius of the centre 
wing frame 40 forward fitting on in-service aeroplanes.
    This condition, if not detected and corrected, could lead to 
reduced structural integrity of the aeroplane.
    To address this unsafe condition, Airbus issued several 
inspection Service Bulletins (SB) and repair instructions. 
Consequently, EASA issued AD 2009-0094, which was later superseded 
by EASA AD 2011-0163 [which corresponds to FAA AD 2012-25-06, 
Amendment 39-17287 (77 FR 75833, December 26, 2012) (``AD 2012-25-
06'')] and [EASA] AD 2014-0199 [which corresponds to the FAA NPRM], 
to require repetitive inspections and corrective actions on the 
affected areas.
    Since those [EASA] ADs were issued, additional in-service 
findings induced Airbus to do a new fatigue analysis, using a 
detailed Finite Element Model study, which resulted in defining new 
inspection methods. Prompted by these results, Airbus issued SB 
A300-57-0261, SB A300-57-6117 and SB A300-57-9034 to introduce these 
inspections. These new inspection SBs supersede and render obsolete 
inspection SB A300-53-0268 and SB A300-57-6052 and the All Operators 
Transmissions (AOT) A300-53A0391, AOT A300-57A6111, AOT A300-53W002-
14 and AOT A300-57W003-14.
    For the reasons described above, EASA issued AD 2015-0232, 
superseding [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
DGAC France AD 1998-038-010(B) R1 [which corresponds to FAA AD 98-
25-07, Amendment 39-10933 (63 FR 68167, December 10, 1998) (``AD 98-
25-07'')] and [DGAC France] AD 2003-189(B), and EASA AD 2011-0163 
and [EASA] AD 2014-0199, to require the new inspections of the 
affected areas within new thresholds and intervals.
    This [EASA] AD is revised to clarify the compliance time(s), 
introducing a Note after paragraph (1), and to alleviate the 
reporting requirements of paragraph (3).

    Required actions include repetitive rototest, ultrasonic, high 
frequency eddy current, special detailed, and liquid penetrant 
inspections, as applicable, of the center wing FR 40 lower outboard 
radius for cracking, and related investigative and corrective actions 
if necessary.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0084.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM 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 AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information:
     Airbus Service Bulletin A300-57-6117, dated May 28, 2015.
     Airbus Service Bulletin A300-57-0261, dated June 11, 2015.
    The service information describes procedures for repetitive 
ultrasonic, rototest, high frequency eddy current, special detailed, 
and liquid penetrant inspections, and related investigative and 
corrective actions. These documents are distinct since they apply to 
different airplane models. 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 29 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost            Cost per product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections..........................  Up to 91 work-hours x    Up to $7,735 per         Up to $224,315 per
                                        $85 per hour = $7,735    inspection cycle.        inspection cycle.
                                        per inspection cycle.
Reporting............................  1 work-hour x $85 per    $85....................  $2,465.
                                        hour = $85.
----------------------------------------------------------------------------------------------------------------


[[Page 24029]]

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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.

Regulatory Findings

    We determined that 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 the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

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):

2017-10-05 Airbus: Amendment 39-18879; Docket No. FAA-2015-0084; 
Directorate Identifier 2014-NM-181-AD.

(a) Effective Date

    This AD is effective June 29, 2017.

(b) Affected ADs

    This AD affects AD 98-25-07, Amendment 39-10933 (63 FR 68167, 
December 10, 1998) (``AD 98-25-07''); and AD 2012-25-06, Amendment 
39-17287 (77 FR 75833, December 26, 2012) (``AD 2012-25-06'').

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (c)(5) of this AD, 
except airplanes on which Airbus Modification 10221 has been 
embodied in production.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracks on the lower outboard 
radius of the center wing frame (FR) 40 forward fitting. We are 
issuing this AD to detect and correct cracking on the FR 40 forward 
fittings, which could result in reduced structural integrity of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections

    Except as provided by paragraph (i)(1) of this AD, at the 
applicable times specified in paragraph 1.E.(2), ``Compliance,'' of 
Airbus Service Bulletin A300-57-0261, dated June 11, 2015; or Airbus 
Service Bulletin A300-57-6117, dated May 28, 2015; accomplish 
rototest, ultrasonic, high frequency eddy current, special detailed, 
and liquid penetrant inspections, as applicable, of the center wing 
FR 40 lower outboard radius for cracking, and do all applicable 
related investigative actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0261, dated June 11, 
2015; or Airbus Service Bulletin A300-57-6117, dated May 28, 2015; 
as applicable. Do all applicable related investigative actions 
before further flight. Repeat the inspections thereafter at the 
applicable times specified in paragraph 1.E. (2), ``Compliance,'' of 
Airbus Service Bulletin A300-57-0261, dated June 11, 2015; or Airbus 
Service Bulletin A300-57-6117, dated May 28, 2015.

(h) Corrective Actions

    If, during any inspection required by paragraph (g) of this AD, 
any crack is found, before further flight, accomplish the applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0261, dated June 11, 
2015; or Airbus Service Bulletin A300-57-6117, dated May 28, 2015; 
as applicable; except as required by paragraph (i)(2) of this AD.

(i) Service Information Exception

    (1) Where the service information specified in paragraph (g) of 
this AD specifies a compliance time ``from this service bulletin 
issuance date,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (2) Where the service information specified in paragraph (h) of 
this AD specifies to contact Airbus for certain conditions, before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus's EASA 
Design Organization Approval (DOA).

(j) No Terminating Action for This AD

    Accomplishing a corrective action required by paragraph (h) of 
this AD, or accomplishing a preventative action specified in Airbus 
Service Bulletin A300-57-0260 or A300-57-6116, as applicable, does 
not terminate the repetitive inspections required by paragraph (g) 
of this AD.

[[Page 24030]]

(k) Terminating Action for Certain Requirements of Other ADs

    (1) Accomplishing the actions required by paragraph (g) of this 
AD terminates the actions required by paragraphs (a) and (b) of AD 
98-25-07.
    (2) Accomplishing the actions required by paragraph (g) of this 
AD terminates the actions required by paragraphs (i) and (j) of AD 
2012-25-06.

(l) Reporting Requirements

    Within 60 days after any inspection required by paragraph (g) of 
this AD, or within 60 days after the effective date of this AD, 
whichever occurs later, report any findings, positive or negative, 
to Airbus Service Bulletin Reporting Online Application on Airbus 
World (https://w3.airbus.com/).

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Reporting Requirements: 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0232R1, dated December 16, 
2015, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-0084.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) 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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-57-0261, dated June 11, 2015.
    (ii) Airbus Service Bulletin A300-57-6117, dated May 28, 2015.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (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 Renton, Washington, on May 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10285 Filed 5-24-17; 8:45 am]
 BILLING CODE 4910-13-P