Airworthiness Directives; Airbus Airplanes, 712-716 [2016-30117]

Download as PDF 712 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations 75373–75377, 3 CFR, 2006 Comp., pp. 216– 200. 2. Section 9301.5 is revised to read as follows: ■ § 9301.5 request Accessing records without Certain SIGAR records, including the agency’s Quarterly Report, audit reports, testimony, oversight plans, press releases, other public issuances, and records that are required by 5 U.S.C. 552(a)(2) to be made publicly available are available electronically from SIGAR’s homepage at http:// www.sigar.mil. SIGAR encourages requesters to visit its Web site before making a request for records under § 9301.6. ■ 3. In § 9301.6, paragraphs (c)(1)(ii), (c)(3)(i), and (d)(1) are revised to read as follows: § 9301.6 Requesting records. jstallworth on DSK7TPTVN1PROD with RULES * * * * * (c) * * * (1) * * * (ii) Request denied. If the FOIA Officer denies the request, in full or part, the FOIA Officer shall provide the requester written notice of the denial together with the approximate number of pages of information withheld and the exemption under which the information was withheld. SIGAR will indicate, if technically feasible, the amount of information deleted and the exemption under which the deletion is made at the place in the record where the deletion was made. SIGAR will also indicate the exemption under which a deletion is made on the released portion of the record, unless including that indication would harm an interest protected by the exemptions. The notice shall also describe the procedure for filing an appeal. SIGAR will further notify the requester of their right to seek assistance from SIGAR’s FOIA Public Liaison or dispute resolution services from the FOIA Public Liaison or the Office of Government Information Services. * * * * * (3) * * * (i) In general. If the FOIA Officer determines that unusual circumstances exist, the FOIA Officer may extend for no more than ten days (except Saturdays, Sundays and Federal holidays) the time limits described in paragraph (c)(1) of this section by providing written notice of the extension to the requester. The FOIA Officer shall include with the notice a brief statement of the reason for the extension and the date the FOIA Officer expects to make the determination. If the extension goes beyond ten working VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 days, the FOIA Officer will include a notification of the requester’s right to seek dispute resolutions services from the Office of Government Information Services. * * * * * (d) * * * (1) Initiating appeals. Requesters not satisfied with the FOIA Officer’s written decision may request SIGAR’s FOIA Appellate Authority to review the decision. Appeals must be delivered in writing within 90 days of the date of the decision and shall be addressed to the FOIA Appellate Authority, Office of Privacy, Records & Disclosure, Special Inspector General for Afghanistan Reconstruction, 2530 Crystal Drive, Arlington, VA 22202. As there may be delays in mail delivery, it is advisable to Fax appeals to (703) 601–3804 or email to sigar.pentagon.gencoun.mbx.foia@ mail.mil. An appeal shall include a statement specifying the records that are the subject of the appeal and explaining why the Appellate Authority should grant the appeal. * * * * * ■ 4. In § 9301.8, paragraph (f)(3) is added to read as follows: § 9301.8 Fees in general. * * * * * (f) * * * (3) SIGAR determines that unusual circumstances apply to the processing of a request, provides timely notice the requester, and delay is excused for an additional ten days, but SIGAR still fails to respond within the timeframe established by the additional delay. This provision applies only to search fees. However, the following exceptions shall apply: (i) Notwithstanding § 9301.8(f)(3), if SIGAR determines that unusual circumstances apply and that responding to the request requires the production of more than 5,000 pages, SIGAR may continue to charge search fees, or duplication fees for requesters in preferred status, for as long as necessary, after timely written notice has been made to the requester and SIGAR has discussed with the requester how the requester could effectively limit the scope of the request via written mail, electronic mail, or telephone, or made three good-faith attempts to do so. (ii) Notwithstanding § 9301.8(f)(3), if a court determines that exceptional circumstances exist, SIGAR’s failure to comply with a time limit shall be excused for the length of time provided by the court order. [FR Doc. 2016–30775 Filed 1–3–17; 8:45 am] BILLING CODE 3710–L9–P PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0143; Directorate Identifier 2012–NM–113–AD; Amendment 39–18753; AD 2016–25–27] 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 all Airbus Model A300 B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R variant F airplanes. This AD was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. This AD requires repetitive detailed inspections for cracking of the lower frame fittings of the frame foot, and replacement with a new frame foot if cracking is found. This AD also provides optional terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 8, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 8, 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.airwortheas@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–2014–0143. 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–2014– 0143; or in person at the Docket Management Facility between 9 a.m. E:\FR\FM\04JAR1.SGM 04JAR1 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 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. 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. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: jstallworth on DSK7TPTVN1PROD with RULES Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A300 B4–603, B4–620, B4–622, B4– 605R, B4–622R, F4–605R, F4–622R, and C4–605R variant F airplanes. The SNPRM published in the Federal Register on July 7, 2016 (81 FR 44241) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on March 19, 2014 (79 FR 15266) (‘‘the NPRM’’). The NPRM was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. The NPRM proposed to require repetitive detailed inspections of the lower frame fittings, related investigative actions, and corrective actions if necessary. The SNPRM proposed to replace the proposed requirements in the NPRM with new repetitive detailed inspections for cracking of the lower frame fittings of the frame foot, and replacement with a new frame foot if cracking is found. The SNPRM also proposed to provide optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct cracking of the lower frame 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 AD 2015–0217, dated October 30, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A300 B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4– VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 605R, F4–622R, and C4–605R variant F airplanes. The MCAI states: During accomplishment of Airbus Service Bulletin (SB) A300–53–6111 (EASA AD 2012–0103), addressing detailed visual inspections of the lower frame fittings between Frame (FR) 41 and FR46, a crack was detected on one A300–600 aeroplane in the area 2 of the foot of FR46 at junction radius level. This frame, previously repaired due to a crack finding in the frame foot area 1, was not due to be inspected before reaching the post-repair inspection threshold, i.e. 45,400 flight cycles since repair embodiment. Further investigation determined that the repairs specified in Airbus SB A300–53–6111 were of limited effect to prevent cracking in the frame foot area 2. This condition, if not detected and corrected, could affect the structural integrity of the fuselage of all aeroplanes operated up to the extended service goal (ESG). As a temporary action and until an improvement of the existing repairs was made available, EASA issued AD 2012–0229 [AD * * *] to require a one-time detailed inspection (DET) of the frame feet that were repaired in accordance with Airbus SB A300–53–6111, and the reporting of findings to Airbus. Since that [EASA] AD was issued, a detailed study was performed resulting in the development of a new inspection programme. Consequently, Airbus cancelled SB A300– 53–6111 and replaced it with SB A300–53– 6177, introducing repetitive DET of the lower frame fittings between FR41 and FR46 for the entire fleet. In addition to this new inspection programme, Airbus designed a new frame foot which can be installed on aeroplanes through Airbus SB A300–53– 6176. For the reasons described above, this [EASA] AD supersedes EASA AD 2012–0103, not retaining its requirements, and instead requires the new inspection programme for the lower frame fittings. This [EASA] AD also introduces an optional terminating action for the repetitive inspections required by the [EASA] AD. Corrective actions include replacing any cracked lower frame fittings with a new frame foot. 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–2014–0143. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM and the FAA’s response to each comment. Request To Extend Compliance Time for Reporting Requirement United Parcel Service (UPS) asked that the compliance time for submitting the inspection report specified in paragraph (h) of the proposed AD (in the PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 713 SNPRM) be extended from 30 to 60 days. UPS stated that accomplishing the inspection may occur many days before the final task signoff (i.e., restoring access due to other work in the area), risking noncompliance with the 30-day requirement. We agree to extend the compliance time for the reporting requirement in this AD to 60 days, because we have determined that this longer compliance time does not affect continued operational safety. We have changed paragraph (i) of this AD accordingly. Request for Clarification of Compliance Time Airbus asked that we clarify the compliance time for the inspections specified in paragraph (g) of the proposed AD (in the SNPRM). Airbus stated that unless Airbus Service Bulletin A300–53–6177, dated May 20, 2015, specifies differently, the inspection thresholds should be counted from the first flight of the airplane, not from the effective date of the AD. Airbus added that the compliance time provided in the proposed AD could be confusing to operators. Airbus also stated that for airplanes on which the inspections have not been done as of the effective date of the AD, no grace period is provided, which is a burden on operators. We agree that clarification is necessary. We agree that the compliance time identified in the ‘‘Threshold’’ column of paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A300–53–6177, dated May 20, 2015, refers to accumulated flight cycles or flight hours on the airplane since its first flight, but only if Airbus Service Bulletin A300–53–6177, dated May 20, 2015, does not specify differently. We redesignated paragraph (h) in the SNPRM as paragraph (i) of this AD, and redesignated subsequent paragraphs accordingly. We added clarification of the compliance times for the thresholds in paragraph (h)(1) of this AD. We acknowledge that a grace period was not provided for all configurations. We removed the grace period exception language from paragraph (g) of the proposed AD (in the SNPRM) and moved it to paragraph (h)(2) of this AD. Paragraph (h)(2) of this AD explains that where grace periods specified in Airbus Service Bulletin A300–53–6177, dated May 20, 2015, refer to the issue date of certain service information, those compliance times are after the effective date of the AD. The exception in paragraph (h)(2) of this AD does not apply to compliance times specified as E:\FR\FM\04JAR1.SGM 04JAR1 714 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations jstallworth on DSK7TPTVN1PROD with RULES thresholds in Airbus Service Bulletin A300–53–6177, dated May 20, 2015. In addition, we have determined that the actions for Configuration 004 airplanes identified in Airbus Service Bulletin A300–53–6177, dated May 20, 2015, must be clarified. For Configuration 004 airplanes identified in Airbus Service Bulletin A300–53– 6177, dated May 20, 2015, the actions required by paragraph (g) of this AD cannot be accomplished in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53– 6177, dated May 20, 2015. Paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A300–53–6177, dated May 20, 2015, specifies the action for Configuration 004 airplanes as contacting and reporting to Airbus. Therefore, we have added paragraph (h)(3) to this AD to require operators to contact 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), for corrective actions for Configuration 004 airplanes. Request for Clarification of Inspections for Airplanes With a Previously Replaced Frame Foot UPS asked for clarification of the inspection requirements specified in paragraph (g) of the proposed AD (in the SNPRM) for airplanes that previously replaced a frame foot per Airbus Service Bulletin A300–53–6111. UPS stated that if cracking was found during the inspections using that service information there were two options available: Installing a reinforcing doubler on the damaged fitting or replacing the fitting with a new part. UPS added that in Airbus Service Bulletin A300–53–6177, dated May 20, 2015, the inspection requirements are defined for airplanes previously inspected and found with no cracks, or fittings repaired per Airbus Service Bulletin A300–53–6111. UPS noted that it is not clear how to address airplanes on which the cracked fittings were replaced instead of installing a reinforcing repair. UPS asked that fittings replaced with a new part per Airbus Service Bulletin A300–53–6111 be treated as a previously inspected fitting with no crack findings, with repetitive inspections done per Airbus Service Bulletin A300–53–6177, dated May 20, 2015, using Configuration 001 instructions. UPS stated that this proposal is conservative and exceeds the inspection requirements in the proposed AD (in the SNPRM). We agree that clarification is necessary. Airbus Service Bulletin VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 A300–53–6177, dated May 20, 2015, defines four configurations: Configuration 001 for a frame foot that was never repaired, Configuration 002 for a frame foot that was preventatively repaired, Configuration 003 for a frame foot repaired in Area 1 as specified in Airbus Service Bulletin A300–53–6111 or with certain other repairs, and Configuration 004 for any frame foot not addressed by Configurations 1 through 3. If a new frame foot is installed on an airplane, it would be classified as Configuration 001. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. 529 work-hours and require parts costing $131,500, for a cost of $176,465. 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. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300–53–6177, dated May 20, 2015. The service information describes procedures for repetitive detailed inspections for cracking of the lower frame fittings between FR41 and FR46. Airbus has also issued Service Bulletin A300–53–6176, dated May 20, 2015. The service information describes procedures for replacing all lower frame feet between frame FR41 and FR46 with new, improved frame feet. 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. 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. Costs of Compliance We estimate that this AD affects 123 airplanes of U.S. registry. We estimate that it takes about 541 work-hours per product to comply with the basic requirements of this AD, and 1 work-hour per product for reporting. The average labor rate is $85 per workhour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $5,666,610, or $46,070 per product. We estimate that the optional terminating modification will take about 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; PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\04JAR1.SGM 04JAR1 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations 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): ■ 2016–25–27 Airbus: Amendment 39–18753; Docket No. FAA–2014–0143; Directorate Identifier 2012–NM–113–AD. (a) Effective Date This AD is effective February 8, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4– 603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R variant F airplanes; certificated in any category; all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. jstallworth on DSK7TPTVN1PROD with RULES (e) Reason This AD was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. We are issuing this AD to detect and correct cracking of the lower frame 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 and Replacement At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A300–53–6177, dated May 20, 2015, except as required by paragraphs VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 (h)(1) and (h)(2) of this AD: Perform a detailed inspection for cracking of the lower frame fittings between frame (FR) 41 and FR46 of the frame foot, and if any crack is found, before further flight, replace with a new frame foot, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6177, dated May 20, 2015, except as required by paragraph (h)(3) of this AD. Repeat the inspection thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A300–53–6177, dated May 20, 2015. (h) Service Information Exceptions (1) Where the threshold identified in the ‘‘Threshold’’ column of paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A300–53–6177, dated May 20, 2015, specifies flight cycles or flight hours without specifying from a repair, replacement, or last inspection, the specified compliance time is accumulated flight cycles or flight hours on the airplane since its first flight. (2) Where Airbus Service Bulletin A300– 53–6177, dated May 20, 2015, specifies a compliance time ‘‘from issuance of revision 04 of Service Bulletin No. A300–53–6111,’’ or ‘‘from issuance of Service Bulletin No. A300–53–6177,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (3) For Configuration 004 airplanes identified in Airbus Service Bulletin A300– 53–6177, dated May 20, 2015: Within 6 months after the effective date of this AD, contact 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), for corrective actions and accomplish all applicable corrective actions using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (i) Reporting At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD: Submit a report of the findings (both positive and negative) of each inspection required by paragraph (g) of this AD. Send the report to Airbus Service Bulletin Reporting Online Application on Airbus World (https:// w3.airbus.com). (1) If the inspection was done on or after the effective date of this AD: Submit the report within 60 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 60 days after the effective date of this AD. (j) Optional Terminating Action Replacement of all lower frame feet between FR41 and FR46, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6176, dated May 20, 2015, terminates the repetitive inspections required by paragraph (g) of this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 715 (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: 425–227–1405; fax: 425–227– 2125. Information may be emailed to: 9ANM-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. The AMOC approval letter must specifically reference this AD. (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 the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (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. (l) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0217, dated October 30, 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–2014–0143. (m) 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. E:\FR\FM\04JAR1.SGM 04JAR1 716 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations (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 A300–53–6176, dated May 20, 2015. (ii) Airbus Service Bulletin A300–53–6177, dated May 20, 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 December 6, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–30117 Filed 1–3–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–0733; Directorate Identifier 2015–SW–040–AD; Amendment 39–18762; AD 2016–26–04] RIN 2120–AA64 Airworthiness Directives; Robinson Helicopter Company Helicopters We are adopting a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44, R44 II, and R66 helicopters. This AD requires inspecting the main rotor blade (MRB). This AD was prompted by a determination that some MRBs may have reduced blade thickness due to blending out corrosion. The actions are intended to prevent the unsafe condition on these products. DATES: This AD is effective February 8, 2017. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of February 8, 2017. jstallworth on DSK7TPTVN1PROD with RULES VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 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– 0733; 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, any incorporated-byreference 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: Eric Schrieber, Aviation Safety Engineer, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone (562) 627– 5348; email eric.schrieber@faa.gov. SUPPLEMENTARY INFORMATION: Discussion Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: For service information identified in this final rule, contact Robinson Helicopter Company, 2901 Airport Drive, Torrance, CA 90505; telephone (310) 539–0508; fax (310) 539–5198; or at http:// www.robinsonheli.com. You may review a copy of 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–2016– 0733. ADDRESSES: On May 27, 2016, at 81 FR 33609, 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 Robinson Model R44 and R44 II helicopters with an MRB part number (P/N) C016–7, Revision N/C, A through Z, and AA through AE; and Model R66 helicopters with an MRB P/N F016–2, Revision A through E. The NPRM proposed to require a one-time visual inspection of the MRB for a crack, corrosion, dent, nick, and scratch and either altering the MRB or removing it from service. The NPRM was prompted by a report of a fatigue crack on a Model R44 II helicopter at the MRB trailing edge that had grown to reach the blade spar. The FAA subsequently determined that PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 some MRBs may have reduced blade fatigue resistance due to repair by blending out corrosion in the area of the crack site radius. The proposed requirements were intended to prevent an MRB fatigue crack, which could lead to MRB failure and subsequent loss of helicopter control. Comments After our NPRM (81 FR 33609, May 27, 2016) was published, we received a comment from one commenter. Request Robinson requested we change the applicability of the AD for part number (P/N) C016–7 from ‘‘Revision N/C, A through Z, and AA through AE’’ to ‘‘Revision AA through AE.’’ Robinson stated that P/N C016–7 did not exist until Revision AA and suggested that some technicians may wrongfully apply the proposed AD to P/N C016–5 Revisions W thru Z. We agree and have revised the AD accordingly. FAA’s Determination We have reviewed the relevant information, considered the comment received, and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed with the change previously described. This change is consistent with the intent of the proposals in the NPRM (81 FR 33609, May 27, 2016) and will not increase the economic burden on any operator nor increase the scope of the AD. Related Service Information Under 1 CFR Part 51 We reviewed Robinson R44 Service Bulletin SB–89, dated March 30, 2015 (SB–89), for Model R44 and R44 II helicopters and Robinson R66 Service Bulletin SB–13, dated March 30, 2015 (SB–13), for Model R66 helicopters. SB– 89 and SB–13 provide a one-time procedure to inspect each MRB for cracks, corrosion, and damage that may indicate a crack. If there is a crack, corrosion, or any damage, SB–89 and SB–13 specify removing the MRB from service and contacting Robinson. Otherwise, SB–89 and SB–13 describe procedures to smooth the transition at the chord increase of each MRB to reduce the stress concentration. 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. E:\FR\FM\04JAR1.SGM 04JAR1

Agencies

[Federal Register Volume 82, Number 2 (Wednesday, January 4, 2017)]
[Rules and Regulations]
[Pages 712-716]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30117]


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

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-113-AD; 
Amendment 39-18753; AD 2016-25-27]
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 all 
Airbus Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, 
F4-622R, and C4-605R variant F airplanes. This AD was prompted by 
reports of cracks in the frame base fittings connecting the frame lower 
positions to the center wing box. This AD requires repetitive detailed 
inspections for cracking of the lower frame fittings of the frame foot, 
and replacement with a new frame foot if cracking is found. This AD 
also provides optional terminating action for the repetitive 
inspections. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective February 8, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 8, 
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-2014-0143.

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-2014-
0143; or in person at the Docket Management Facility between 9 a.m.

[[Page 713]]

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 all Airbus 
Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, 
and C4-605R variant F airplanes. The SNPRM published in the Federal 
Register on July 7, 2016 (81 FR 44241) (``the SNPRM''). We preceded the 
SNPRM with a notice of proposed rulemaking (NPRM) that published in the 
Federal Register on March 19, 2014 (79 FR 15266) (``the NPRM''). The 
NPRM was prompted by reports of cracks in the frame base fittings 
connecting the frame lower positions to the center wing box. The NPRM 
proposed to require repetitive detailed inspections of the lower frame 
fittings, related investigative actions, and corrective actions if 
necessary. The SNPRM proposed to replace the proposed requirements in 
the NPRM with new repetitive detailed inspections for cracking of the 
lower frame fittings of the frame foot, and replacement with a new 
frame foot if cracking is found. The SNPRM also proposed to provide 
optional terminating action for the repetitive inspections. We are 
issuing this AD to detect and correct cracking of the lower frame 
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 AD 
2015-0217, dated October 30, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition on all Airbus Model A300 B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F 
airplanes. The MCAI states:

    During accomplishment of Airbus Service Bulletin (SB) A300-53-
6111 (EASA AD 2012-0103), addressing detailed visual inspections of 
the lower frame fittings between Frame (FR) 41 and FR46, a crack was 
detected on one A300-600 aeroplane in the area 2 of the foot of FR46 
at junction radius level.
    This frame, previously repaired due to a crack finding in the 
frame foot area 1, was not due to be inspected before reaching the 
post-repair inspection threshold, i.e. 45,400 flight cycles since 
repair embodiment.
    Further investigation determined that the repairs specified in 
Airbus SB A300-53-6111 were of limited effect to prevent cracking in 
the frame foot area 2.
    This condition, if not detected and corrected, could affect the 
structural integrity of the fuselage of all aeroplanes operated up 
to the extended service goal (ESG).
    As a temporary action and until an improvement of the existing 
repairs was made available, EASA issued AD 2012-0229 [AD * * *] to 
require a one-time detailed inspection (DET) of the frame feet that 
were repaired in accordance with Airbus SB A300-53-6111, and the 
reporting of findings to Airbus.
    Since that [EASA] AD was issued, a detailed study was performed 
resulting in the development of a new inspection programme.
    Consequently, Airbus cancelled SB A300-53-6111 and replaced it 
with SB A300-53-6177, introducing repetitive DET of the lower frame 
fittings between FR41 and FR46 for the entire fleet. In addition to 
this new inspection programme, Airbus designed a new frame foot 
which can be installed on aeroplanes through Airbus SB A300-53-6176.
    For the reasons described above, this [EASA] AD supersedes EASA 
AD 2012-0103, not retaining its requirements, and instead requires 
the new inspection programme for the lower frame fittings. This 
[EASA] AD also introduces an optional terminating action for the 
repetitive inspections required by the [EASA] AD.

    Corrective actions include replacing any cracked lower frame 
fittings with a new frame foot. 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-2014-0143.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the SNPRM and 
the FAA's response to each comment.

Request To Extend Compliance Time for Reporting Requirement

    United Parcel Service (UPS) asked that the compliance time for 
submitting the inspection report specified in paragraph (h) of the 
proposed AD (in the SNPRM) be extended from 30 to 60 days. UPS stated 
that accomplishing the inspection may occur many days before the final 
task signoff (i.e., restoring access due to other work in the area), 
risking noncompliance with the 30-day requirement.
    We agree to extend the compliance time for the reporting 
requirement in this AD to 60 days, because we have determined that this 
longer compliance time does not affect continued operational safety. We 
have changed paragraph (i) of this AD accordingly.

Request for Clarification of Compliance Time

    Airbus asked that we clarify the compliance time for the 
inspections specified in paragraph (g) of the proposed AD (in the 
SNPRM). Airbus stated that unless Airbus Service Bulletin A300-53-6177, 
dated May 20, 2015, specifies differently, the inspection thresholds 
should be counted from the first flight of the airplane, not from the 
effective date of the AD. Airbus added that the compliance time 
provided in the proposed AD could be confusing to operators. Airbus 
also stated that for airplanes on which the inspections have not been 
done as of the effective date of the AD, no grace period is provided, 
which is a burden on operators.
    We agree that clarification is necessary.
    We agree that the compliance time identified in the ``Threshold'' 
column of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin 
A300-53-6177, dated May 20, 2015, refers to accumulated flight cycles 
or flight hours on the airplane since its first flight, but only if 
Airbus Service Bulletin A300-53-6177, dated May 20, 2015, does not 
specify differently. We redesignated paragraph (h) in the SNPRM as 
paragraph (i) of this AD, and redesignated subsequent paragraphs 
accordingly. We added clarification of the compliance times for the 
thresholds in paragraph (h)(1) of this AD.
    We acknowledge that a grace period was not provided for all 
configurations. We removed the grace period exception language from 
paragraph (g) of the proposed AD (in the SNPRM) and moved it to 
paragraph (h)(2) of this AD. Paragraph (h)(2) of this AD explains that 
where grace periods specified in Airbus Service Bulletin A300-53-6177, 
dated May 20, 2015, refer to the issue date of certain service 
information, those compliance times are after the effective date of the 
AD. The exception in paragraph (h)(2) of this AD does not apply to 
compliance times specified as

[[Page 714]]

thresholds in Airbus Service Bulletin A300-53-6177, dated May 20, 2015.
    In addition, we have determined that the actions for Configuration 
004 airplanes identified in Airbus Service Bulletin A300-53-6177, dated 
May 20, 2015, must be clarified. For Configuration 004 airplanes 
identified in Airbus Service Bulletin A300-53-6177, dated May 20, 2015, 
the actions required by paragraph (g) of this AD cannot be accomplished 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6177, dated May 20, 2015. Paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 20, 
2015, specifies the action for Configuration 004 airplanes as 
contacting and reporting to Airbus. Therefore, we have added paragraph 
(h)(3) to this AD to require operators to contact 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), for corrective actions for Configuration 
004 airplanes.

Request for Clarification of Inspections for Airplanes With a 
Previously Replaced Frame Foot

    UPS asked for clarification of the inspection requirements 
specified in paragraph (g) of the proposed AD (in the SNPRM) for 
airplanes that previously replaced a frame foot per Airbus Service 
Bulletin A300-53-6111. UPS stated that if cracking was found during the 
inspections using that service information there were two options 
available: Installing a reinforcing doubler on the damaged fitting or 
replacing the fitting with a new part. UPS added that in Airbus Service 
Bulletin A300-53-6177, dated May 20, 2015, the inspection requirements 
are defined for airplanes previously inspected and found with no 
cracks, or fittings repaired per Airbus Service Bulletin A300-53-6111. 
UPS noted that it is not clear how to address airplanes on which the 
cracked fittings were replaced instead of installing a reinforcing 
repair. UPS asked that fittings replaced with a new part per Airbus 
Service Bulletin A300-53-6111 be treated as a previously inspected 
fitting with no crack findings, with repetitive inspections done per 
Airbus Service Bulletin A300-53-6177, dated May 20, 2015, using 
Configuration 001 instructions. UPS stated that this proposal is 
conservative and exceeds the inspection requirements in the proposed AD 
(in the SNPRM).
    We agree that clarification is necessary. Airbus Service Bulletin 
A300-53-6177, dated May 20, 2015, defines four configurations: 
Configuration 001 for a frame foot that was never repaired, 
Configuration 002 for a frame foot that was preventatively repaired, 
Configuration 003 for a frame foot repaired in Area 1 as specified in 
Airbus Service Bulletin A300-53-6111 or with certain other repairs, and 
Configuration 004 for any frame foot not addressed by Configurations 1 
through 3. If a new frame foot is installed on an airplane, it would be 
classified as Configuration 001. We have not changed this AD in this 
regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously, and 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-53-6177, dated May 20, 
2015. The service information describes procedures for repetitive 
detailed inspections for cracking of the lower frame fittings between 
FR41 and FR46. Airbus has also issued Service Bulletin A300-53-6176, 
dated May 20, 2015. The service information describes procedures for 
replacing all lower frame feet between frame FR41 and FR46 with new, 
improved frame feet. 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 123 airplanes of U.S. registry.
    We estimate that it takes about 541 work-hours per product to 
comply with the basic requirements of this AD, and 1 work-hour per 
product for reporting. The average labor rate is $85 per work-hour. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $5,666,610, or $46,070 per product.
    We estimate that the optional terminating modification will take 
about 529 work-hours and require parts costing $131,500, for a cost of 
$176,465.

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;

[[Page 715]]

    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):

2016-25-27 Airbus: Amendment 39-18753; Docket No. FAA-2014-0143; 
Directorate Identifier 2012-NM-113-AD.

(a) Effective Date

    This AD is effective February 8, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F airplanes; 
certificated in any category; all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracks in the frame base 
fittings connecting the frame lower positions to the center wing 
box. We are issuing this AD to detect and correct cracking of the 
lower frame 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 and Replacement

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 
20, 2015, except as required by paragraphs (h)(1) and (h)(2) of this 
AD: Perform a detailed inspection for cracking of the lower frame 
fittings between frame (FR) 41 and FR46 of the frame foot, and if 
any crack is found, before further flight, replace with a new frame 
foot, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-53-6177, dated May 20, 2015, except as 
required by paragraph (h)(3) of this AD. Repeat the inspection 
thereafter at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 
20, 2015.

(h) Service Information Exceptions

    (1) Where the threshold identified in the ``Threshold'' column 
of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-
53-6177, dated May 20, 2015, specifies flight cycles or flight hours 
without specifying from a repair, replacement, or last inspection, 
the specified compliance time is accumulated flight cycles or flight 
hours on the airplane since its first flight.
    (2) Where Airbus Service Bulletin A300-53-6177, dated May 20, 
2015, specifies a compliance time ``from issuance of revision 04 of 
Service Bulletin No. A300-53-6111,'' or ``from issuance of Service 
Bulletin No. A300-53-6177,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.
    (3) For Configuration 004 airplanes identified in Airbus Service 
Bulletin A300-53-6177, dated May 20, 2015: Within 6 months after the 
effective date of this AD, contact 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), for corrective actions and accomplish 
all applicable corrective actions using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA.

(i) Reporting

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD: Submit a report of the findings (both positive and 
negative) of each inspection required by paragraph (g) of this AD. 
Send the report to Airbus Service Bulletin Reporting Online 
Application on Airbus World (https://w3.airbus.com).
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 60 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 60 days after the effective date of 
this AD.

(j) Optional Terminating Action

    Replacement of all lower frame feet between FR41 and FR46, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6176, dated May 20, 2015, terminates the repetitive 
inspections required by paragraph (g) of this AD.

(k) 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: 425-227-1405; fax: 425-227-2125. 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. The 
AMOC approval letter must specifically reference this AD.
    (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 the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (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.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0217, dated October 30, 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-
2014-0143.

(m) 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.

[[Page 716]]

    (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 A300-53-6176, dated May 20, 2015.
    (ii) Airbus Service Bulletin A300-53-6177, dated May 20, 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 December 6, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30117 Filed 1-3-17; 8:45 am]
 BILLING CODE 4910-13-P