Airworthiness Directives; Airbus Airplanes, 56526-56532 [2014-22467]

Download as PDF 56526 Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules submissions at http:// www.regulations.gov as well as enter the comment submissions into ADAMS. The NRC does not routinely edit comment submissions to remove identifying or contact information. If you are requesting or aggregating comments from other persons for submission to the NRC, then you should inform those persons not to include identifying or contact information that they do not want to be publicly disclosed in their comment submission. Your request should state that the NRC does not routinely edit comment submissions to remove such information before making the comment submissions available to the public or entering the comment submissions into ADAMS. II. The Petition Anthony R. Pietrangelo, Vice President, and Chief Nuclear Officer, NEI, submitted a PRM dated June 12, 2014 (ADAMS Accession No. ML14184B120), requesting that the NRC revise its cyber security requirements. Specifically, the petitioner requests that the NRC revise 10 CFR 73.54(a) to ensure the regulation is not overly burdensome for NRC licensees, and adequately protects the public health and safety and common defense and security. The petitioner requests that the NRC promptly initiate rulemaking to resolve this matter. The NRC has determined that the petition meets the threshold sufficiency requirements for a petition for rulemaking under 10 CFR 2.802 ‘‘Petition for rulemaking,’’ and the petition has been docketed as PRM–73– 18. The NRC is requesting public comment on the petition for rulemaking. asabaliauskas on DSK5VPTVN1PROD with RULES III. The Petitioner The petition states that NEI ‘‘is responsible for establishing a unified industry position on matters affecting the nuclear energy industry, including the regulatory aspects of generic operational and technical issues.’’ The petition further states that ‘‘NEI member companies are specifically affected by the NRC’s cyber security regulations.’’ The NEI claims it provides a ‘‘principal interface between power reactor licensees and the NRC on matters of policy, including cyber security-related policy.’’ IV. Discussion of the Petition The petitioner states that power reactor licensees are required to establish and maintain a physical protection program to protect against the design basis threat of radiological sabotage, and summarizes the physical protection program and the attributes of VerDate Sep<11>2014 16:54 Sep 19, 2014 Jkt 232001 the design basis threat of radiological sabotage described in 10 CFR 73.1, which include: (1) An external physical assault, (2) an internal threat, (3) a land vehicle bomb assault, (4) a waterborne vehicle bomb assault, and (5) a cyber attack. The petitioner asserts that to prevent radiological sabotage, licensees have well-established programs to identify the set of personnel systems, and equipment that must be protected against the design basis threat in order to prevent significant core damage and spent fuel sabotage. The petitioner noted that NRC’s cyber security requirements, found in 10 CFR 73.54, provide the programmatic requirements to defend against the design basis threat of radiological sabotage through a cyber attack, and that Section 73.54(a)(1) requires licensees to protect certain digital assets against cyber attack even though those digital assets, if compromised, would not adversely impact the systems and equipment necessary to prevent significant core damage and spent fuel sabotage. The petitioner asserts that the current regulations require NRC licensees to protect one set of systems and equipment against the effects of four of the attributes of the design basis threat (physical assault; internal threat; land vehicle bomb assault; waterborne vehicle bomb assault), and a substantially broader set of assets against the fifth design basis threat attribute, cyber attack. Further, the petitioner contends that this regulatory language is inconsistent with both the agency’s intent in promulgating the cyber security requirements and the NRC’s programmatic requirements to defend against other attributes of the radiological sabotage design basis threat. The petitioner argues that the language in 10 CFR 73.54(a)(1) unnecessarily diverts NRC licensee attention and resources away from the protection of assets that have a nexus to radiological safety. The petitioner asserts that this provision burdens NRC reactor licensees without providing a commensurate enhancement in the protection of the public health and safety, or plant security. Furthermore, the petitioner claims that for digital assets that do not reasonably require protection against radiological sabotage, the considerable time, resources, and cost needed to protect them against cyber attack is unjustified. In this regard, the petitioner asserts that the current cyber security regulations fail to comply with the Commission’s Principles of Good Regulation. The petitioner states that the industry has brought to the attention of the NRC staff the significant problems created by PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 the current scoping language in 10 CFR 73.54(a), and has determined that revisions to NRC regulations are needed to address this problem. The petitioner further states that implementing the revisions proposed herein will not adversely affect NRC licensees’ ability to ensure that public health, safety, and security are being adequately protected. NEI contends that the change proposed in its petition is the single most important near-term regulatory improvement that can be made in the area of cyber security. The petitioner claims that it would provide a substantial benefit to regulatory clarity and stability by assuring that licensees have protected those assets that, if compromised by a cyber attack, would be inimical to the health and safety of the public. The complete text of the petition is available for review as described in Section I.A. of this document. Because the petitioner has satisfied the docketing criteria in 10 CFR 2.802, ‘‘Petition for rulemaking,’’ the NRC has docketed this petition as PRM–73–18. The NRC is reviewing the issues raised by the petitioner to determine whether they should be considered in the NRC’s rulemaking process. Dated at Rockville, Maryland, this 15th day of September, 2014. For the Nuclear Regulatory Commission. Annette L. Vietti-Cook, Secretary of the Commission. [FR Doc. 2014–22523 Filed 9–19–14; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0648; Directorate Identifier 2013–NM–136–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2010–06– 04, for certain Airbus Model A300 B2– 1C, B2–203, B2K–3C, B4–103, B4–203, B4–2C airplanes; Model A310 series airplanes; Model A300 B4–600 series airplanes; and Model A300 B4–600R series airplanes. AD 2010–06–04 currently requires repetitive inspections to detect cracks of the pylon side panels SUMMARY: E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules asabaliauskas on DSK5VPTVN1PROD with RULES (upper section) at rib 8; and corrective actions if necessary. Since we issued AD 2010–06–04, fleet survey and updated fatigue and damage tolerance analyses were done. We have determined that reduced compliance times are necessary. This proposed AD would continue to require repetitive inspections for cracking of the pylons 1 and 2 side panels (upper section) at rib 8 with reduced compliance times, and corrective actions if necessary. This proposed AD would also require repetitive post-repair and postmodification inspections and repair if necessary. This proposed AD would also remove certain airplanes having a certain modification from the applicability. We are proposing this AD to detect and correct cracking of pylon side panels (upper section) at rib 8, which could lead to reduced structural integrity of the pylon primary structure, which could cause detachment of the engine from the fuselage. DATES: We must receive comments on this proposed AD by November 6, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 proposed AD, the VerDate Sep<11>2014 16:54 Sep 19, 2014 Jkt 232001 regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0648; Directorate Identifier 2013–NM–136–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On March 4, 2010, we issued AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572). AD 2010– 06–04 requires actions intended to address an unsafe condition on Airbus Model A300 B2–1C, B2–203, B2K–3C, B4–103, B4–203, B4–2C airplanes; Model A310 series airplanes; Model A300 B4–600 series airplanes; and Model A300 B4–600R series airplanes. Since we issued AD 2010–06–04, fleet survey and updated fatigue and damage tolerance analyses were done. We have determined that reduced compliance times are necessary. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0136R1, dated July 30, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Cracks were found on pylon side panels (upper section) at rib 8 on Airbus A300, A310 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 56527 and A300–600 aeroplanes equipped with General Electric engines. Investigation of these findings indicated that this problem was likely to also affect aeroplanes of this type design with other engine installations. This condition, if not detected and corrected, could lead to reduced strength of the pylon primary structure, possibly resulting in pylon structural failure and inflight loss of an engine. Prompted by these findings, EASA issued AD 2008–0181 [http://www.regulations.gov/ #!documentDetail;D=FAA-2009-0789-0002] [which corresponds to FAA AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)] to require repetitive detailed visual inspections [of the pylon side panels (upper section) at rib 8] and, depending on aeroplane configuration and/or findings, the accomplishment of applicable corrective action(s). Since that [EASA] AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300–600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the risk for these aeroplanes is higher than initially determined and consequently, the threshold and interval must be reduced to allow timely detection of these cracks and the accomplishment of applicable correction action(s). EASA issued AD 2013–0136 [http:// ad.easa.europa.eu/ad/2013-0136R1] which retained the requirements of EASA AD 2008– 0181, which was superseded, and required the inspections to be accomplished within reduced thresholds and intervals. After publication of EASA AD 2013–0136, it appeared that Airbus Mod 03599 had no influence on the aeroplane configuration affected by this AD. At the same time Airbus Service Bulletin (SB) A300–54–6015 Revision 3 was not integrally taken into account as this revision no longer identifies configuration 3 aeroplanes. For the reasons described above, EASA 2013–0136 is revised to exclude Airbus Mod 03599 from the applicability and to delete the reference to the configuration 3 for A300–600 aeroplanes. Corrective actions include doing a repair. This proposed AD also provides an optional modification (installing a doubler), which would terminate the repetitive inspections. Required actions also include repetitive post-repair and post-modification inspections and repair if necessary. Depending on airplane configuration: Initial compliance times range from 4,800 flight cycles or 24,100 flight hours, and 9,700 flight cycles or 19,400 flight hours. Initial post-modification and post-repair inspection compliance times range from 7,200 flight cycles or 36,400 flight hours, and 10,400 flight cycles or 50,800 flight hours, depending on inspection type. Repetitive intervals range from 2,600 flight cycles or 13,000 flight hours, and 6,700 flight cycles or 18,700 flight hours. You may examine E:\FR\FM\22SEP1.SGM 22SEP1 56528 Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2014–0648. Relevant Service Information Airbus has issued the Service Bulletins listed below. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. • Airbus Service Bulletin A300–54– 0075, Revision 03, dated March 27, 2013. • Airbus Service Bulletin A300–54– 6015, Revision 03, dated April 11, 2013. • Airbus Service Bulletin A310–54– 2018, Revision 03, dated April 11, 2013. • Airbus Service Bulletin A300–54– 0081, dated August 11, 1993. • Airbus Service Bulletin A300–54– 6021, Revision 02, dated May 21, 2008. • Airbus Service Bulletin A310–54– 2024, dated August 11, 1993. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. proposed AD, this proposed AD would require that you repair any cracking before further flight. Differences Between This Proposed AD and the MCAI or Service Information Although the MCAI or service information allows further flight after cracks are found during compliance with the required actions of this Costs of Compliance Changes to This NPRM Table 2, ‘‘Service Bulletins,’’ in AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010), has been converted to text in paragraph (g)(9) of this AD. Table 3, ‘‘Previous Service Information,’’ in AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010), has been converted to text in paragraph (m)(1) of this AD. We estimate that this proposed AD affects 156 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection [retained actions from AD 2010–06– 04, Amendment 39–16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)]. Inspection [new proposed actions] ..................... 4 work-hours × $85 per hour = $340. $0 24 work-hours × $85 per hour = $2,040 per inspection cycle. 0 We estimate the following costs to do any necessary repairs that would be Parts cost Cost per product Cost on U.S. operators $340 ............................. $53,040. $2,040 per inspection cycle. $318,240 per inspection cycle. required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs: ON-CONDITION COSTS Labor cost Parts cost Repair ........................................................................ Optional Modification ................................................. asabaliauskas on DSK5VPTVN1PROD with RULES Action 58 work-hours × $85 per hour = $4,930 ................... Up to 48 work-hours × $85 per hour = $4,080 ......... $3,910 .............. Up to $1,026 ..... 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 VerDate Sep<11>2014 16:54 Sep 19, 2014 Jkt 232001 that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Cost per product $8,840. Up to $5,106. 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules 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. Amend § 39.13 by removing Airworthiness Directive (AD) 2010–06– 04, Amendment 39–16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572), and adding the following new AD: ■ Airbus: Docket No. FAA–2014–0648; Directorate Identifier 2013–NM–136–AD. (a) Comments Due Date We must receive comments by November 6, 2014. (b) Affected ADs This AD replaces AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Airbus Model A300 B2–1C, B2–203, B2K–3C, B4–103, B4–203, and B4–2C airplanes, on which Airbus Modification 02434 has been embodied in production. (2) Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes, except those on which Airbus Modification 10432 has been embodied in production. (3) Airbus Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes, except those on which Airbus Modification 10432 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/Pylons. (e) Reason This AD was prompted by reports of cracks found on pylon side panels at rib 8 and a fleet survey and updated fatigue and damage tolerance analyses. We are issuing this AD to detect and correct cracking of pylon side panels (upper section) at rib 8, which could lead to reduced structural integrity of the pylon primary structure, which could cause detachment of the engine from the fuselage. 56529 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Actions and Compliance With Revised Service Information This paragraph restates the requirements of paragraph (f) of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572), with revised service information. Accomplishing the initial inspection required by paragraph (h) of this AD terminates the requirements of this paragraph. (1) For Configuration 01 airplanes as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in table 1 to paragraph (g) of this AD, except as required by paragraphs (g)(2) and (g)(3) of this AD, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of this AD or paragraphs (k)(1), (k)(2), or (k)(3) of this AD. Repeat the inspection at the time specified in table 1 to paragraph (g) of this AD. TABLE 1—TO PARAGRAPH (G) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES For Model— That have accumulated— Inspect before the accumulation of— Or within— And repeat the inspection at intervals not to exceed— Whichever occurs later ≤17,500 total flight A300 B4–103, B4–203, and B4–2C airplanes. A300 B4–103, B4–203, and B4–2C airplanes. asabaliauskas on DSK5VPTVN1PROD with RULES A300 B2–1C, B2–203, and B2K–3C airplanes. A300 B2–1C, B2–203, and B2K–3C airplanes. ≤18,000 total flight cycles 1 A300 B4–601, B4–603, B4–605R, B4–620, B4– 622, and B4–622R airplanes. A300 B4–601, B4–603, B4–605R, B4–620, B4– 622, and B4–622R airplanes. A310–200 airplanes with GE CF6–80A3 or Pratt & Whitney engines. A310–200 airplanes with GE CF6–80A3 or Pratt & Whitney engines. A310–200 airplanes with GE CF6–80C2 engines. ≤18,000 total flight cycles 1 A310–200 airplanes with GE CF6–80C2 engines. >18,000 total flight cycles 1 A310–300 SR 3 airplanes with Pratt & Whitney JT9D engines. ≤18,000 total flight cycles 1 VerDate Sep<11>2014 cycles 1 5,350 total flight cycles ..... 2,500 flight cycles 2 ........... 4,300 flight cycles. >17,500 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 5,350 total flight cycles ..... 250 flight cycles 2 .............. 4,300 flight cycles. 2,000 flight cycles 2 ........... 4,300 flight cycles. 250 flight cycles 2 .............. 4,300 flight cycles. 2,000 flight cycles 2 ........... 3,600 flight cycles. >18,000 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 4,200 total flight cycles ..... >18,000 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 3,600 flight cycles. ≤18,000 total flight cycles 1 9,700 total flight cycles or 19,400 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 7,800 total flight cycles or 15,600 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 8,600 total flight cycles or 24,000 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 6,700 flight cycles or 13,400 flight hours, whichever occurs first. 6,700 flight cycles or 13,400 flight hours, whichever occurs first. 5,800 flight cycles or 11,600 flight hours, whichever occurs first. 5,800 flight cycles or 11,600 flight hours, whichever occurs first. 6,700 flight cycles or 18,700 flight hours, whichever occurs first. >18,000 total flight cycles 1 ≤18,000 total flight cycles 1 16:54 Sep 19, 2014 Jkt 232001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... E:\FR\FM\22SEP1.SGM 22SEP1 56530 Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules TABLE 1—TO PARAGRAPH (G) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES—Continued A310–300 SR 3 airplanes with Pratt & Whitney JT9D engines. A310–300 SR 3 airplanes with GE engines. >18,000 total flight cycles 1 A310–300 SR 3 airplanes with GE engines. >18,000 total flight cycles 1 A310–300 SR 3 airplanes with Pratt & Whitney 4000 engines. A310–300 SR 3 airplanes with Pratt & Whitney 4000 engines. A310–300 LR 4 airplanes with Pratt & Whitney JT9D engines. A310–300 LR 4 airplanes with Pratt & Whitney JT9D engines. A310–300 LR 4 airplanes with GE engines. ≤18,000 total flight cycles 1 A310–300 LR 4 airplanes with GE engines. >18,000 total flight cycles 1 A310–300 LR 4 airplanes with Pratt & Whitney 4000 engines. A310–300 LR 4 airplanes with Pratt & Whitney 4000 engines. ≤18,000 total flight cycles 1 ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 5,900 total flight cycles or 29,500 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 4,800 total flight cycles or 24,100 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 4,800 total flight cycles or 24,000 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 6,700 flight cycles or 18,700 flight hours, whichever occurs first. 5,700 flight cycles or 15,900 flight hours, whichever occurs first. 5,700 flight cycles or 15,900 flight hours, whichever occurs first. 5,800 flight cycles or 16,200 flight hours, whichever occurs first. 5,800 flight cycles or 16,200 flight hours, whichever occurs first. 6,000 flight cycles or 30,300 flight hours, whichever occurs first. 6,000 flight cycles or 30,300 flight hours, whichever occurs first. 5,100 flight cycles or 25,500 flight hours, whichever occurs first. 5,100 flight cycles or 25,500 flight hours, whichever occurs first. 5,200 flight cycles or 26,300 flight hours, whichever occurs first. 5,200 flight cycles or 26,300 flight hours, whichever occurs first. 1 As of April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010)). April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010)). 3 ‘‘SR’’ applies to airplanes with average flights less than 4 flight hours. 4 ‘‘LR’’ refers to airplanes with average flights of 4 or more flight hours. asabaliauskas on DSK5VPTVN1PROD with RULES 2 After (2) For Model A300 and A300–600 airplanes that have accumulated more than 40,000 total flight hours as of April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010)): Within 250 flight cycles after April 15, 2010, do the actions specified in paragraph (g)(1) of this AD. (3) For Model A310 airplanes that have accumulated more than 55,500 total flight hours as of April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010)): Within 250 flight cycles after April 15, 2010, do the actions specified in paragraph (g)(1) of this AD. (4) For Configuration 01 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: If a crack is found during any inspection required by paragraph (g)(1) of this AD, before further flight, install a doubler, in accordance with paragraph 3.C. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. (5) For Configuration 02 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or within 250 flight cycles after April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 VerDate Sep<11>2014 16:54 Sep 19, 2014 Jkt 232001 (75 FR 11428, March 11, 2010)), whichever occurs later, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. (6) For Configuration 03 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or within 250 flight cycles after April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010)), whichever occurs later, perform a detailed visual inspection, and a high frequency eddy current inspection as applicable, of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. (7) For Configuration 02 and 03 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: If a crack is found during any inspection required by paragraph (g)(1), (g)(5), or (g)(6) of this AD, before further flight, repair in accordance with paragraph 3.C. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (8) For all airplanes, except those in Configuration 01, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: Repeat the inspection specified in paragraph (g)(1), (g)(5), or (g)(6) of this AD, as applicable, at the intervals specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of this AD. (9) For the actions specified in paragraph (g) of this AD, use the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or paragraph (k)(1), (k)(2), or (k)(3) of this AD. (i) Airbus Mandatory Service Bulletin A300–54–0075, excluding Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model A300 B2–1C, B2–203, B2K–3C, B4– 103, B4–203, and B4–2C airplanes). (ii) Airbus Mandatory Service Bulletin A300–54–6015, excluding Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model A300 B4–601, B4–603, B4–605R, B4– 620, B4–622, and B4–622R airplanes). (iii) Airbus Mandatory Service Bulletin A310–54–2018, excluding Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (for Model A310 series airplanes). (h) New Repetitive Inspections and Repair Except as required by paragraphs (l)(1) and (l)(2) of this AD, at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of the applicable service bulletin identified in E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules paragraph (k) of this AD: Do a detailed inspection for cracking of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraph (g)(1) through (g)(9) of this AD. (1) If any cracking is found, before further flight, do a high frequency eddy current (HFEC) inspection to confirm the crack, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD. (i) If any crack indication is confirmed during the HFEC inspection specified in paragraph (h)(1) of this AD, and the crack is less than 20 mm, before further flight, repair, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD. (ii) If any crack indication is confirmed during the HFEC inspection specified in paragraph (h)(1) of this AD and the crack is greater than or equal to 20 mm, 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). (2) If no cracking is found, or if crack indication is not confirmed during the HFEC inspection required by paragraph (h)(1) of this AD, at the applicable interval specified in paragraph 1.E., ‘‘Compliance,’’ of the applicable service bulletin identified in paragraph (k) of this AD, repeat the inspection specified in paragraph (h) of this AD, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD until the modification specified in paragraph (i) is done. asabaliauskas on DSK5VPTVN1PROD with RULES (i) Optional Modification Modifying by installing a doubler on the left hand (LH) pylon 1 and right hand (RH) pylon 2, on pylon side panels (upper section), at rib 8, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–54–0081, dated August 11, 1993; A310–54–2024, dated August 11, 1993; or A300–54–6021, Revision 02, dated May 21, 2008; as applicable, terminates the repetitive inspections specified in paragraph (h)(2) of this AD. (j) Post-Modification and Post-Repair Repetitive Inspections and Corrective Actions For airplanes on which the modification has been done as specified in paragraph (i) of this AD, and airplanes on which the repair has been done as specified in paragraph (h) of this AD: At the applicable compliance time specified in paragraph 1.E., Compliance,’’ of the applicable service bulletin identified in paragraph (k) of this AD, do the post-modification and post-repair detailed inspections for cracking, as applicable, of the LH and RH side panels of pylons 1 and 2, in accordance with the applicable service bulletins identified in paragraph (k) of this AD. Repeat the VerDate Sep<11>2014 16:54 Sep 19, 2014 Jkt 232001 inspections thereafter at the times specified in paragraph 1.E., ‘‘Compliance’’ of the applicable service bulletin specified in paragraph (k) of this AD. If any cracking is found, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA Design Organization Approval (DOA). This repair is not a terminating action for the repetitive inspections required by this paragraph. (k) New Service Information Use the applicable service bulletin identified in paragraphs (k)(1) through (k)(3) of this AD to accomplish the inspections required by paragraphs (h) and (j) of this AD. (1) Airbus Mandatory Service Bulletin A300–54–0075, Revision 03, dated March 27, 2013 (for Model A300 B2–1C, B2–203, B2K– 3C, B4–103, B4–203, and B4–2C airplanes). (2) Airbus Mandatory Service Bulletin A310–54–2018, Revision 03, dated April 11, 2013 (for Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes). (3) Airbus Mandatory Service Bulletin A300–54–6015, Revision 03, dated April 11, 2013 (for Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622, and B4–622R airplanes). (l) Exceptions (1) Where the compliance time column in the tables in paragraph 1.E., ‘‘Compliance,’’ of the applicable service bulletin identified in paragraph (k) of this AD specifies a ‘‘threshold’’ in FC or FH, and does not specify from repair or service bulletin embodiment, those compliance times are total flight cycles and total flight hours. (2) Where the tables in paragraph 1.E., ‘‘Compliance,’’ of the applicable service bulletin specified in paragraph (k) of this AD specifies ‘‘grace period after the receipt of the service bulletin,’’ this AD requires compliance within the corresponding compliance time after the effective date of this AD. (m) Credit for Previous Actions (1) This paragraph restates the credit provided by paragraph (f)(9) of AD 2010–06– 04, Amendment 39–16228 (75 FR 11428, March 11, 2010) with no changes. This paragraph provides credit for initial inspections required by paragraph (g) of this AD, if those actions were performed prior to April 15, 2010 (the effective date of AD 2010–06–04) using the applicable service bulletins specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, which are not incorporated by reference in this AD. (i) Airbus Service Bulletin A300–54–0075, dated August 11, 1993. (ii) Airbus Service Bulletin A300–54–0075, Revision 01, dated November 9, 2007. (iii) Airbus Service Bulletin A300–54– 6015, dated August 11, 1993. (iv) Airbus Service Bulletin A300–54– 6015, Revision 01, dated November 9, 2007. (v) Airbus Service Bulletin A310–54–2018, dated August 11, 1993. (vi) Airbus Service Bulletin A310–54– 2018, Revision 01, dated November 16, 2007. (2) This paragraph provides credit for initial inspections required by paragraph (h) PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 56531 of this AD, if those actions were performed before the effective date of this AD using the applicable service bulletins specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD. (i) Airbus Service Bulletin A300–54–0075, dated August 11, 1993, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A300–54–0075, Revision 01, dated November 9, 2007, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A300–54– 0075, Revision 02, dated June 26, 2008, which is incorporated by reference in this AD. (iv) Airbus Service Bulletin A300–54– 6015, dated August 11, 1993, which is not incorporated by reference in this AD. (v) Airbus Service Bulletin A300–54–6015, Revision 01, dated November 9, 2007, which is not incorporated by reference in this AD. (vi) Airbus Service Bulletin A300–54– 6015, Revision 02, dated June 26, 2008, which is incorporated by reference in this AD. (vii) Airbus Service Bulletin A310–54– 2018, dated August 11, 1993, which is not incorporated by reference in this AD. (viii) Airbus Service Bulletin A310–54– 2018, Revision 01, dated November 16, 2007, which is not incorporated by reference in this AD. (ix) Airbus Service Bulletin A310–54– 2018, Revision 02, dated June 26, 2008, which is incorporated by reference in this AD. (3) This paragraph provides credit for initial inspections required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service bulletins specified in paragraphs (m)(3)(i) and (m)(3)(ii) of this AD. (i) Airbus Service Bulletin A300–54–6021, dated August 11, 1993. (ii) Airbus Service Bulletin A300–54–6021, Revision 01, dated November 16, 2007. (n) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: 9ANM-116-AMOC-REQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2010–06–04, Amendment 39–16228 (75 FR E:\FR\FM\22SEP1.SGM 22SEP1 56532 Federal Register / Vol. 79, No. 183 / Monday, September 22, 2014 / Proposed Rules 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572); are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0136R1, dated July 30, 2013, 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 it in Docket No. FAA–2014–0648. (2) 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. 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. Issued in Renton, Washington, on September 12, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–22467 Filed 9–19–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 890 [Docket No. FDA–2000–N–0158] Reclassification of Iontophoresis Devices Intended for Any Other Purposes AGENCY: Food and Drug Administration, Proposed order. The Food and Drug Administration (FDA) is proposing to reclassify iontophoresis devices intended for any other purposes, a preamendments class III device, into class II (special controls), and to amend the device identification. FDA is proposing this reclassification on its own initiative based on new information. This action implements certain statutory requirements. asabaliauskas on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 16:54 Sep 19, 2014 Jkt 232001 Electronic Submissions Submit electronic comments in the following way: • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. Written Submissions Submit written submissions in the following ways: • Mail/Hand delivery/Courier (for paper submissions): Division of Dockets Management (HFA–305), Food and Drug Administration, 5630 Fishers Lane, Rm. 1061, Rockville, MD 20852. Instructions: All submissions received must include the Docket No. (FDA– 2000–N–0158) for this rulemaking. All comments received may be posted without change to http:// www.regulations.gov, including any personal information provided. For additional information on submitting comments, see the ‘‘Comments’’ heading of the SUPPLEMENTARY INFORMATION section of this document. Docket: For access to the docket to read background documents or comments received, go to http:// www.regulations.gov and insert the docket number, found in brackets in the heading of this document, into the ‘‘Search’’ box and follow the prompts and/or go to the Division of Dockets Management, 5630 Fishers Lane, Rm. 1061, Rockville, MD 20852. FOR FURTHER INFORMATION CONTACT: Michael Ryan, Center for Devices and Radiological Health, Food and Drug Administration,10903 New Hampshire Ave., Bldg. 66, Rm. 1615, Silver Spring, MD 20993–0002, 301–796–6283. SUPPLEMENTARY INFORMATION: I. Background—Regulatory Authorities HHS. ACTION: Submit either electronic or written comments by December 22, 2014. See section XII for the proposed effective date of a final order based on this proposed order. ADDRESSES: You may submit comments by any of the following methods: DATES: The Federal Food, Drug, and Cosmetic Act (the FD&C Act), as amended by the Medical Device Amendments of 1976 (the 1976 amendments) (Pub. L. 94– 295), the Safe Medical Devices Act of 1990 (Pub. L. 101–629), the Food and Drug Administration Modernization Act of 1997 (Pub. L. 105–115), the Medical Device User Fee and Modernization Act of 2002 (Pub. L. 107–250), the Medical Devices Technical Corrections Act (Pub. L. 108–214), the Food and Drug Administration Amendments Act of 2007 (Pub. L. 110–85), and the Food and Drug Administration Safety and PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Innovation Act (FDASIA) (Pub. L. 112– 144), among other amendments, established a comprehensive system for the regulation of medical devices intended for human use. Section 513 of the FD&C Act (21 U.S.C. 360c) established three categories (classes) of devices, reflecting the regulatory controls needed to provide reasonable assurance of their safety and effectiveness. The three categories of devices are class I (general controls), class II (special controls), and class III (premarket approval). Section 513(a)(1) of the FD&C Act defines class II devices as those devices for which the general controls by themselves are insufficient to provide reasonable assurance of safety and effectiveness, but for which there is sufficient information to establish special controls to provide such assurance. Under section 513 of the FD&C Act, devices that were in commercial distribution before the enactment of the 1976 amendments, May 28, 1976 (generally referred to as preamendments devices), are classified after FDA has: (1) Received a recommendation from a device classification panel (an FDA advisory committee); (2) published the panel’s recommendation for comment, along with a proposed regulation classifying the device; and (3) published a final regulation classifying the device. FDA has classified most preamendments devices under these procedures. Devices that were not in commercial distribution prior to May 28, 1976 (generally referred to as postamendments devices) are automatically classified by section 513(f) of the FD&C Act into class III without any FDA rulemaking process. Those devices remain in class III and require premarket approval unless, and until, the device is reclassified into class I or II or FDA issues an administrative order finding the device to be substantially equivalent, in accordance with section 513(i) of the FD&C Act, to a predicate device that does not require premarket approval. The Agency determines whether new devices are substantially equivalent to predicate devices by means of premarket notification procedures in section 510(k) of the FD&C Act (21 U.S.C. 360(k)) and part 807 (21 CFR part 807). On July 9, 2012, FDASIA was enacted. Section 608(a) of FDASIA amended section 513(e) of the FD&C Act, changing the process for reclassifying a device from rulemaking to an administrative order. Section 513(e) of the FD&C Act governs reclassification of classified preamendments devices. This E:\FR\FM\22SEP1.SGM 22SEP1

Agencies

[Federal Register Volume 79, Number 183 (Monday, September 22, 2014)]
[Proposed Rules]
[Pages 56526-56532]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-22467]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0648; Directorate Identifier 2013-NM-136-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2010-06-
04, for certain Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-
203, B4-2C airplanes; Model A310 series airplanes; Model A300 B4-600 
series airplanes; and Model A300 B4-600R series airplanes. AD 2010-06-
04 currently requires repetitive inspections to detect cracks of the 
pylon side panels

[[Page 56527]]

(upper section) at rib 8; and corrective actions if necessary. Since we 
issued AD 2010-06-04, fleet survey and updated fatigue and damage 
tolerance analyses were done. We have determined that reduced 
compliance times are necessary. This proposed AD would continue to 
require repetitive inspections for cracking of the pylons 1 and 2 side 
panels (upper section) at rib 8 with reduced compliance times, and 
corrective actions if necessary. This proposed AD would also require 
repetitive post-repair and post-modification inspections and repair if 
necessary. This proposed AD would also remove certain airplanes having 
a certain modification from the applicability. We are proposing this AD 
to detect and correct cracking of pylon side panels (upper section) at 
rib 8, which could lead to reduced structural integrity of the pylon 
primary structure, which could cause detachment of the engine from the 
fuselage.

DATES: We must receive comments on this proposed AD by November 6, 
2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0648; 
Directorate Identifier 2013-NM-136-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On March 4, 2010, we issued AD 2010-06-04, Amendment 39-16228 (75 
FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572). AD 
2010-06-04 requires actions intended to address an unsafe condition on 
Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C 
airplanes; Model A310 series airplanes; Model A300 B4-600 series 
airplanes; and Model A300 B4-600R series airplanes.
    Since we issued AD 2010-06-04, fleet survey and updated fatigue and 
damage tolerance analyses were done. We have determined that reduced 
compliance times are necessary. The European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2013-
0136R1, dated July 30, 2013 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for the specified products. The MCAI states:

    Cracks were found on pylon side panels (upper section) at rib 8 
on Airbus A300, A310 and A300-600 aeroplanes equipped with General 
Electric engines. Investigation of these findings indicated that 
this problem was likely to also affect aeroplanes of this type 
design with other engine installations.
    This condition, if not detected and corrected, could lead to 
reduced strength of the pylon primary structure, possibly resulting 
in pylon structural failure and in-flight loss of an engine.
    Prompted by these findings, EASA issued AD 2008-0181 [http://www.regulations.gov/#!documentDetail;D=FAA-2009-0789-0002] [which 
corresponds to FAA AD 2010-06-04, Amendment 39-16228 (75 FR 11428, 
March 11, 2010); corrected May 4, 2010 (75 FR 23572)] to require 
repetitive detailed visual inspections [of the pylon side panels 
(upper section) at rib 8] and, depending on aeroplane configuration 
and/or findings, the accomplishment of applicable corrective 
action(s).
    Since that [EASA] AD was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analyses have been performed in order 
to substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. The results of these analyses have shown that the risk for 
these aeroplanes is higher than initially determined and 
consequently, the threshold and interval must be reduced to allow 
timely detection of these cracks and the accomplishment of 
applicable correction action(s).
    EASA issued AD 2013-0136 [http://ad.easa.europa.eu/ad/2013-0136R1] which retained the requirements of EASA AD 2008-0181, which 
was superseded, and required the inspections to be accomplished 
within reduced thresholds and intervals.
    After publication of EASA AD 2013-0136, it appeared that Airbus 
Mod 03599 had no influence on the aeroplane configuration affected 
by this AD. At the same time Airbus Service Bulletin (SB) A300-54-
6015 Revision 3 was not integrally taken into account as this 
revision no longer identifies configuration 3 aeroplanes.
    For the reasons described above, EASA 2013-0136 is revised to 
exclude Airbus Mod 03599 from the applicability and to delete the 
reference to the configuration 3 for A300-600 aeroplanes.

    Corrective actions include doing a repair. This proposed AD also 
provides an optional modification (installing a doubler), which would 
terminate the repetitive inspections. Required actions also include 
repetitive post-repair and post-modification inspections and repair if 
necessary.
    Depending on airplane configuration: Initial compliance times range 
from 4,800 flight cycles or 24,100 flight hours, and 9,700 flight 
cycles or 19,400 flight hours. Initial post-modification and post-
repair inspection compliance times range from 7,200 flight cycles or 
36,400 flight hours, and 10,400 flight cycles or 50,800 flight hours, 
depending on inspection type. Repetitive intervals range from 2,600 
flight cycles or 13,000 flight hours, and 6,700 flight cycles or 18,700 
flight hours. You may examine

[[Page 56528]]

the MCAI in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2014-0648.

Relevant Service Information

    Airbus has issued the Service Bulletins listed below. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.
     Airbus Service Bulletin A300-54-0075, Revision 03, dated 
March 27, 2013.
     Airbus Service Bulletin A300-54-6015, Revision 03, dated 
April 11, 2013.
     Airbus Service Bulletin A310-54-2018, Revision 03, dated 
April 11, 2013.
     Airbus Service Bulletin A300-54-0081, dated August 11, 
1993.
     Airbus Service Bulletin A300-54-6021, Revision 02, dated 
May 21, 2008.
     Airbus Service Bulletin A310-54-2024, dated August 11, 
1993.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Although the MCAI or service information allows further flight 
after cracks are found during compliance with the required actions of 
this proposed AD, this proposed AD would require that you repair any 
cracking before further flight.

Changes to This NPRM

    Table 2, ``Service Bulletins,'' in AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010), has been converted to text in 
paragraph (g)(9) of this AD.
    Table 3, ``Previous Service Information,'' in AD 2010-06-04, 
Amendment 39-16228 (75 FR 11428, March 11, 2010), has been converted to 
text in paragraph (m)(1) of this AD.

Costs of Compliance

    We estimate that this proposed AD affects 156 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                  Cost per
            Action                Labor cost      Parts cost      product            Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection [retained actions   4 work-hours x             $0  $340...........  $53,040.
 from AD 2010-06-04,            $85 per hour =
 Amendment 39-16228 (75 FR      $340.
 11428, March 11, 2010);
 corrected May 4, 2010 (75 FR
 23572)].
Inspection [new proposed       24 work-hours x             0  $2,040 per       $318,240 per inspection cycle.
 actions].                      $85 per hour =                 inspection
                                $2,040 per                     cycle.
                                inspection
                                cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                      Labor cost               Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Repair............................  58 work-hours x $85    $3,910....................  $8,840.
                                     per hour = $4,930.
Optional Modification.............  Up to 48 work-hours x  Up to $1,026..............  Up to $5,106.
                                     $85 per hour =
                                     $4,080.
----------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

[[Page 56529]]

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. Amend Sec.  39.13 by removing Airworthiness Directive (AD) 2010-06-
04, Amendment 39-16228 (75 FR 11428, March 11, 2010); corrected May 4, 
2010 (75 FR 23572), and adding the following new AD:

Airbus: Docket No. FAA-2014-0648; Directorate Identifier 2013-NM-
136-AD.

(a) Comments Due Date

    We must receive comments by November 6, 2014.

(b) Affected ADs

    This AD replaces AD 2010-06-04, Amendment 39-16228 (75 FR 11428, 
March 11, 2010); corrected May 4, 2010 (75 FR 23572).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
    (1) Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and 
B4-2C airplanes, on which Airbus Modification 02434 has been 
embodied in production.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes, except those on which Airbus Modification 10432 
has been embodied in production.
    (3) Airbus Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, 
and B4-622R airplanes, except those on which Airbus Modification 
10432 has been embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

(e) Reason

    This AD was prompted by reports of cracks found on pylon side 
panels at rib 8 and a fleet survey and updated fatigue and damage 
tolerance analyses. We are issuing this AD to detect and correct 
cracking of pylon side panels (upper section) at rib 8, which could 
lead to reduced structural integrity of the pylon primary structure, 
which could cause detachment of the engine from the fuselage.

(f) Compliance

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

(g) Retained Actions and Compliance With Revised Service Information

    This paragraph restates the requirements of paragraph (f) of AD 
2010-06-04, Amendment 39-16228 (75 FR 11428, March 11, 2010); 
corrected May 4, 2010 (75 FR 23572), with revised service 
information. Accomplishing the initial inspection required by 
paragraph (h) of this AD terminates the requirements of this 
paragraph.
    (1) For Configuration 01 airplanes as identified in the 
applicable service bulletin identified in paragraph (g)(9) of this 
AD: At the applicable time specified in table 1 to paragraph (g) of 
this AD, except as required by paragraphs (g)(2) and (g)(3) of this 
AD, perform a detailed visual inspection of the pylons 1 and 2 side 
panels (upper section) at rib 8, in accordance with paragraph 3.B. 
of the Accomplishment Instructions of the applicable service 
bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of 
this AD or paragraphs (k)(1), (k)(2), or (k)(3) of this AD. Repeat 
the inspection at the time specified in table 1 to paragraph (g) of 
this AD.

              Table 1--to Paragraph (g) of This AD--Compliance Times for Configuration 1 Airplanes
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
           For Model--                 That have      Inspect before the      Or within--       And repeat the
                                     accumulated--     accumulation of--                         inspection at
                                                                                                intervals not to
                                                                                                    exceed--
                                                     ----------------------------------------
                                                              Whichever occurs later
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2-203, and B2K-3C    <=17,500 total      5,350 total flight  2,500 flight        4,300 flight
 airplanes.                        flight cycles \1\.  cycles.             cycles \2\.         cycles.
A300 B2-1C, B2-203, and B2K-3C    >17,500 total       20,000 total        250 flight cycles   4,300 flight
 airplanes.                        flight cycles \1\.  flight cycles or    \2\.                cycles.
                                                       40,000 total
                                                       flight hours,
                                                       whichever occurs
                                                       first.
A300 B4-103, B4-203, and B4-2C    <=18,000 total      5,350 total flight  2,000 flight        4,300 flight
 airplanes.                        flight cycles \1\.  cycles.             cycles \2\.         cycles.
A300 B4-103, B4-203, and B4-2C    >18,000 total       20,000 total        250 flight cycles   4,300 flight
 airplanes.                        flight cycles \1\.  flight cycles or    \2\.                cycles.
                                                       40,000 total
                                                       flight hours,
                                                       whichever occurs
                                                       first.
A300 B4-601, B4-603, B4-605R, B4- <=18,000 total      4,200 total flight  2,000 flight        3,600 flight
 620, B4-622, and B4-622R          flight cycles \1\.  cycles.             cycles \2\.         cycles.
 airplanes.
A300 B4-601, B4-603, B4-605R, B4- >18,000 total       20,000 total        250 flight cycles   3,600 flight
 620, B4-622, and B4-622R          flight cycles \1\.  flight cycles or    \2\.                cycles.
 airplanes.                                            40,000 total
                                                       flight hours,
                                                       whichever occurs
                                                       first.
A310-200 airplanes with GE CF6-   <=18,000 total      9,700 total flight  1,500 flight        6,700 flight
 80A3 or Pratt & Whitney engines.  flight cycles \1\.  cycles or 19,400    cycles \2\.         cycles or 13,400
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.
A310-200 airplanes with GE CF6-   >18,000 total       19,500 total        250 flight cycles   6,700 flight
 80A3 or Pratt & Whitney engines.  flight cycles \1\.  flight cycles or    \2\.                cycles or 13,400
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-200 airplanes with GE CF6-   <=18,000 total      7,800 total flight  1,500 flight        5,800 flight
 80C2 engines.                     flight cycles \1\.  cycles or 15,600    cycles \2\.         cycles or 11,600
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.
A310-200 airplanes with GE CF6-   >18,000 total       19,500 total        250 flight cycles   5,800 flight
 80C2 engines.                     flight cycles \1\.  flight cycles or    \2\.                cycles or 11,600
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 SR \3\ airplanes with    <=18,000 total      8,600 total flight  1,500 flight        6,700 flight
 Pratt & Whitney JT9D engines.     flight cycles \1\.  cycles or 24,000    cycles \2\.         cycles or 18,700
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.

[[Page 56530]]

 
A310-300 SR \3\ airplanes with    >18,000 total       19,500 total        250 flight cycles   6,700 flight
 Pratt & Whitney JT9D engines.     flight cycles \1\.  flight cycles or    \2\.                cycles or 18,700
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 SR \3\ airplanes with    <=18,000 total      7,000 total flight  1,500 flight        5,700 flight
 GE engines.                       flight cycles \1\.  cycles or 19,600    cycles \2\.         cycles or 15,900
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.
A310-300 SR \3\ airplanes with    >18,000 total       19,500 total        250 flight cycles   5,700 flight
 GE engines.                       flight cycles \1\.  flight cycles or    \2\.                cycles or 15,900
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 SR \3\ airplanes with    <=18,000 total      7,000 total flight  1,500 flight        5,800 flight
 Pratt & Whitney 4000 engines.     flight cycles \1\.  cycles or 19,600    cycles \2\.         cycles or 16,200
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.
A310-300 SR \3\ airplanes with    >18,000 total       19,500 total        250 flight cycles   5,800 flight
 Pratt & Whitney 4000 engines.     flight cycles \1\.  flight cycles or    \2\.                cycles or 16,200
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 LR \4\ airplanes with    <=18,000 total      5,900 total flight  1,500 flight        6,000 flight
 Pratt & Whitney JT9D engines.     flight cycles \1\.  cycles or 29,500    cycles \2\.         cycles or 30,300
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.
A310-300 LR \4\ airplanes with    >18,000 total       19,500 total        250 flight cycles   6,000 flight
 Pratt & Whitney JT9D engines.     flight cycles \1\.  flight cycles or    \2\.                cycles or 30,300
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 LR \4\ airplanes with    <=18,000 total      4,800 total flight  1,500 flight        5,100 flight
 GE engines.                       flight cycles \1\.  cycles or 24,100    cycles \2\.         cycles or 25,500
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.
A310-300 LR \4\ airplanes with    >18,000 total       19,500 total        250 flight cycles   5,100 flight
 GE engines.                       flight cycles \1\.  flight cycles or    \2\.                cycles or 25,500
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 LR \4\ airplanes with    <=18,000 total      4,800 total flight  1,500 flight        5,200 flight
 Pratt & Whitney 4000 engines.     flight cycles \1\.  cycles or 24,000    cycles \2\.         cycles or 26,300
                                                       total flight                            flight hours,
                                                       hours, whichever                        whichever occurs
                                                       occurs first.                           first.
A310-300 LR \4\ airplanes with    >18,000 total       19,500 total        250 flight cycles   5,200 flight
 Pratt & Whitney 4000 engines.     flight cycles \1\.  flight cycles or    \2\.                cycles or 26,300
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
----------------------------------------------------------------------------------------------------------------
\1\ As of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11,
  2010)).
\2\ After April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11,
  2010)).
\3\ ``SR'' applies to airplanes with average flights less than 4 flight hours.
\4\ ``LR'' refers to airplanes with average flights of 4 or more flight hours.

    (2) For Model A300 and A300-600 airplanes that have accumulated 
more than 40,000 total flight hours as of April 15, 2010 (the 
effective date of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, 
March 11, 2010)): Within 250 flight cycles after April 15, 2010, do 
the actions specified in paragraph (g)(1) of this AD.
    (3) For Model A310 airplanes that have accumulated more than 
55,500 total flight hours as of April 15, 2010 (the effective date 
of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11, 2010)): 
Within 250 flight cycles after April 15, 2010, do the actions 
specified in paragraph (g)(1) of this AD.
    (4) For Configuration 01 airplanes, as identified in the 
applicable service bulletin identified in paragraph (g)(9) of this 
AD: If a crack is found during any inspection required by paragraph 
(g)(1) of this AD, before further flight, install a doubler, in 
accordance with paragraph 3.C. of the Accomplishment Instructions of 
the applicable service bulletin identified in paragraph (g)(9) of 
this AD.
    (5) For Configuration 02 airplanes, as identified in the 
applicable service bulletin identified in paragraph (g)(9) of this 
AD: At the applicable time specified in paragraph 1.E.(2) of the 
applicable service bulletin identified in paragraphs (g)(9)(i) 
through (g)(9)(iii) of this AD, or within 250 flight cycles after 
April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010)), whichever occurs later, 
perform a detailed visual inspection of the pylons 1 and 2 side 
panels (upper section) at rib 8, in accordance with paragraph 3.B. 
of the Accomplishment Instructions of the applicable service 
bulletin identified in paragraph (g)(9) of this AD.
    (6) For Configuration 03 airplanes, as identified in the 
applicable service bulletin identified in paragraph (g)(9) of this 
AD: At the applicable time specified in paragraph 1.E.(2) of the 
applicable service bulletin identified in paragraphs (g)(9)(i) 
through (g)(9)(iii) of this AD, or within 250 flight cycles after 
April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010)), whichever occurs later, 
perform a detailed visual inspection, and a high frequency eddy 
current inspection as applicable, of the pylons 1 and 2 side panels 
(upper section) at rib 8, in accordance with paragraph 3.B. of the 
Accomplishment Instructions of the applicable service bulletin 
identified in paragraph (g)(9) of this AD.
    (7) For Configuration 02 and 03 airplanes, as identified in the 
applicable service bulletin identified in paragraph (g)(9) of this 
AD: If a crack is found during any inspection required by paragraph 
(g)(1), (g)(5), or (g)(6) of this AD, before further flight, repair 
in accordance with paragraph 3.C. of the Accomplishment Instructions 
of the applicable service bulletin identified in paragraph (g)(9) of 
this AD.
    (8) For all airplanes, except those in Configuration 01, as 
identified in the applicable service bulletin identified in 
paragraph (g)(9) of this AD: Repeat the inspection specified in 
paragraph (g)(1), (g)(5), or (g)(6) of this AD, as applicable, at 
the intervals specified in paragraph 1.E.(2) of the applicable 
service bulletin identified in paragraph (g)(9)(i) through 
(g)(9)(iii) of this AD.
    (9) For the actions specified in paragraph (g) of this AD, use 
the applicable service bulletin identified in paragraphs (g)(9)(i) 
through (g)(9)(iii) of this AD, or paragraph (k)(1), (k)(2), or 
(k)(3) of this AD.
    (i) Airbus Mandatory Service Bulletin A300-54-0075, excluding 
Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model 
A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes).
    (ii) Airbus Mandatory Service Bulletin A300-54-6015, excluding 
Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model 
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
airplanes).
    (iii) Airbus Mandatory Service Bulletin A310-54-2018, excluding 
Appendices 1, 2, and 3, Revision 02, dated June 26, 2008 (for Model 
A310 series airplanes).

(h) New Repetitive Inspections and Repair

    Except as required by paragraphs (l)(1) and (l)(2) of this AD, 
at the applicable times specified in paragraph 1.E., ``Compliance,'' 
of the applicable service bulletin identified in

[[Page 56531]]

paragraph (k) of this AD: Do a detailed inspection for cracking of 
the pylons 1 and 2 side panels (upper section) at rib 8, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraph (k) of this AD. 
Accomplishing the inspection required by this paragraph terminates 
the requirements of paragraph (g)(1) through (g)(9) of this AD.
    (1) If any cracking is found, before further flight, do a high 
frequency eddy current (HFEC) inspection to confirm the crack, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraph (k) of this AD.
    (i) If any crack indication is confirmed during the HFEC 
inspection specified in paragraph (h)(1) of this AD, and the crack 
is less than 20 mm, before further flight, repair, in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin identified in paragraph (k) of this AD.
    (ii) If any crack indication is confirmed during the HFEC 
inspection specified in paragraph (h)(1) of this AD and the crack is 
greater than or equal to 20 mm, 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).
    (2) If no cracking is found, or if crack indication is not 
confirmed during the HFEC inspection required by paragraph (h)(1) of 
this AD, at the applicable interval specified in paragraph 1.E., 
``Compliance,'' of the applicable service bulletin identified in 
paragraph (k) of this AD, repeat the inspection specified in 
paragraph (h) of this AD, in accordance with the Accomplishment 
Instructions of the applicable service bulletin identified in 
paragraph (k) of this AD until the modification specified in 
paragraph (i) is done.

(i) Optional Modification

    Modifying by installing a doubler on the left hand (LH) pylon 1 
and right hand (RH) pylon 2, on pylon side panels (upper section), 
at rib 8, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-54-0081, dated August 11, 1993; A310-
54-2024, dated August 11, 1993; or A300-54-6021, Revision 02, dated 
May 21, 2008; as applicable, terminates the repetitive inspections 
specified in paragraph (h)(2) of this AD.

(j) Post-Modification and Post-Repair Repetitive Inspections and 
Corrective Actions

    For airplanes on which the modification has been done as 
specified in paragraph (i) of this AD, and airplanes on which the 
repair has been done as specified in paragraph (h) of this AD: At 
the applicable compliance time specified in paragraph 1.E., 
Compliance,'' of the applicable service bulletin identified in 
paragraph (k) of this AD, do the post-modification and post-repair 
detailed inspections for cracking, as applicable, of the LH and RH 
side panels of pylons 1 and 2, in accordance with the applicable 
service bulletins identified in paragraph (k) of this AD. Repeat the 
inspections thereafter at the times specified in paragraph 1.E., 
``Compliance'' of the applicable service bulletin specified in 
paragraph (k) of this AD. If any cracking is found, before further 
flight, repair using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA Design Organization Approval (DOA). This repair is not 
a terminating action for the repetitive inspections required by this 
paragraph.

(k) New Service Information

    Use the applicable service bulletin identified in paragraphs 
(k)(1) through (k)(3) of this AD to accomplish the inspections 
required by paragraphs (h) and (j) of this AD.
    (1) Airbus Mandatory Service Bulletin A300-54-0075, Revision 03, 
dated March 27, 2013 (for Model A300 B2-1C, B2-203, B2K-3C, B4-103, 
B4-203, and B4-2C airplanes).
    (2) Airbus Mandatory Service Bulletin A310-54-2018, Revision 03, 
dated April 11, 2013 (for Model A310-203, -204, -221, -222, -304, -
322, -324, and -325 airplanes).
    (3) Airbus Mandatory Service Bulletin A300-54-6015, Revision 03, 
dated April 11, 2013 (for Model A300 B4-601, B4-603, B4-605R, B4-
620, B4-622, and B4-622R airplanes).

(l) Exceptions

    (1) Where the compliance time column in the tables in paragraph 
1.E., ``Compliance,'' of the applicable service bulletin identified 
in paragraph (k) of this AD specifies a ``threshold'' in FC or FH, 
and does not specify from repair or service bulletin embodiment, 
those compliance times are total flight cycles and total flight 
hours.
    (2) Where the tables in paragraph 1.E., ``Compliance,'' of the 
applicable service bulletin specified in paragraph (k) of this AD 
specifies ``grace period after the receipt of the service 
bulletin,'' this AD requires compliance within the corresponding 
compliance time after the effective date of this AD.

(m) Credit for Previous Actions

    (1) This paragraph restates the credit provided by paragraph 
(f)(9) of AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11, 
2010) with no changes. This paragraph provides credit for initial 
inspections required by paragraph (g) of this AD, if those actions 
were performed prior to April 15, 2010 (the effective date of AD 
2010-06-04) using the applicable service bulletins specified in 
paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, which are not 
incorporated by reference in this AD.
    (i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993.
    (ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated 
November 9, 2007.
    (iii) Airbus Service Bulletin A300-54-6015, dated August 11, 
1993.
    (iv) Airbus Service Bulletin A300-54-6015, Revision 01, dated 
November 9, 2007.
    (v) Airbus Service Bulletin A310-54-2018, dated August 11, 1993.
    (vi) Airbus Service Bulletin A310-54-2018, Revision 01, dated 
November 16, 2007.
    (2) This paragraph provides credit for initial inspections 
required by paragraph (h) of this AD, if those actions were 
performed before the effective date of this AD using the applicable 
service bulletins specified in paragraphs (m)(2)(i) through 
(m)(2)(vi) of this AD.
    (i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993, 
which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated 
November 9, 2007, which is not incorporated by reference in this AD.
    (iii) Airbus Service Bulletin A300-54-0075, Revision 02, dated 
June 26, 2008, which is incorporated by reference in this AD.
    (iv) Airbus Service Bulletin A300-54-6015, dated August 11, 
1993, which is not incorporated by reference in this AD.
    (v) Airbus Service Bulletin A300-54-6015, Revision 01, dated 
November 9, 2007, which is not incorporated by reference in this AD.
    (vi) Airbus Service Bulletin A300-54-6015, Revision 02, dated 
June 26, 2008, which is incorporated by reference in this AD.
    (vii) Airbus Service Bulletin A310-54-2018, dated August 11, 
1993, which is not incorporated by reference in this AD.
    (viii) Airbus Service Bulletin A310-54-2018, Revision 01, dated 
November 16, 2007, which is not incorporated by reference in this 
AD.
    (ix) Airbus Service Bulletin A310-54-2018, Revision 02, dated 
June 26, 2008, which is incorporated by reference in this AD.
    (3) This paragraph provides credit for initial inspections 
required by paragraph (i) of this AD, if those actions were 
performed before the effective date of this AD using the applicable 
service bulletins specified in paragraphs (m)(3)(i) and (m)(3)(ii) 
of this AD.
    (i) Airbus Service Bulletin A300-54-6021, dated August 11, 1993.
    (ii) Airbus Service Bulletin A300-54-6021, Revision 01, dated 
November 16, 2007.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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.
    (i) 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.
    (ii) AMOCs approved previously for AD 2010-06-04, Amendment 39-
16228 (75 FR

[[Page 56532]]

11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572); are 
approved as AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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 Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0136R1, dated July 30, 
2013, 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 it in Docket No. FAA-2014-0648.
    (2) 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. 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.

    Issued in Renton, Washington, on September 12, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-22467 Filed 9-19-14; 8:45 am]
BILLING CODE 4910-13-P