Airworthiness Directives; Airbus Airplanes, 25249-25254 [2015-10177]

Download as PDF Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Fokker Services B.V.: Docket No. FAA– 2015–0933; Directorate Identifier 2014– NM–098–AD. (a) Comments Due Date We must receive comments by June 18, 2015. (b) Affected ADs None. (c) Applicability This AD applies to Fokker Services B.V. Model F.27 Mark 200, 300, 400, 500, 600, and 700 airplanes, certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Reason This AD was prompted by a design review, which revealed that no controlled bonding provisions are present on a number of critical locations inside the fuel tank or connected to the fuel tank wall; and no anti-spray cover is installed on the fuel shut-off valve (FSOV) in both wings. We are issuing this AD to prevent an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Installation of Bonding Provisions and Anti-Spray Cover At the next scheduled opening of the fuel tanks after the effective date of this AD, but no later than 84 months after the effective date of this AD: Install additional bonding provisions at the applicable locations, and install an anti-spray cover on the FSOV in both wings, using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. tkelley on DSK3SPTVN1PROD with PROPOSALS (h) Revision of Maintenance or Inspection Program Within 30 days after installing the bonding provisions and anti-spray cover specified in paragraph (g) of this AD: Revise the airplane maintenance or inspection program, as applicable, by incorporating fuel airworthiness limitation items and Critical Design Configuration Control Limitations (CDCCLs), using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. (i) No Alternative Actions, Intervals, and/or CDCCLs After accomplishing the revision required by paragraph (h) of this AD, no alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are approved as an alternative method of compliance (AMOC) in VerDate Sep<11>2014 17:53 May 01, 2015 Jkt 235001 accordance with the procedures specified in paragraph (j) of this AD. ACTION: (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch; ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1137. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Fokker Services B.V.’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. 25249 SUMMARY: (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0099, dated April 30, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2015–0933. Issued in Renton, Washington, on April 17, 2015. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–10180 Filed 5–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0937; Directorate Identifier 2014–NM–024–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 Notice of proposed rulemaking (NPRM). We propose to supersede Airworthiness Directive (AD) 2011–24– 05, for certain Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–200 and –300 series airplanes. AD 2011–24– 05 currently requires repetitive inspections for cracking of the hole(s) of the horizontal flange of the keel beam, and repair if necessary. Since we issued AD 2011–24–05, a determination was made that the rototest inspection and applicable corrective actions of a certain fastener hole were inadvertently omitted from the requirements in that AD. This proposed AD would change the inspection compliance times, and, for certain airplanes, would add a one-time ultrasonic inspection for cracking at a certain fastener hole. This proposed AD would also provide optional terminating action for the repetitive inspections. We are proposing this AD to detect and correct cracking of the fastener holes, which could result in rupture of the keel beam, and consequent reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 18, 2015. 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—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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:// E:\FR\FM\04MYP1.SGM 04MYP1 25250 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules www.regulations.gov by searching for and locating Docket No. FAA–2015– 0937; 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 Operations 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; 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–2015–0937; Directorate Identifier 2014–NM–024–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. tkelley on DSK3SPTVN1PROD with PROPOSALS Discussion On November 7, 2011, we issued AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), for certain Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–200 and –300 series airplanes. AD 2011–24–05 requires actions intended to address the unsafe condition on the products listed above. Since we issued AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0010R1, dated May 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, VerDate Sep<11>2014 17:53 May 01, 2015 Jkt 235001 or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–200 and –300 series airplanes. The MCAI states: During A330 and A340 aeroplanes fatigue tests, cracks were detected on the RH [righthand] and LH [left-hand] sides between the crossing area of the keel beam fitting and the front spar of the Centre Wing Box (CWB). This condition, if not detected and corrected, could lead to keel beam rupture which would affect the area structural integrity of the area. Prompted by this potential unsafe condition, EASA issued AD 2006–0315 [http://ad.easa.europa.eu/blob/easa_ad_ 2006_0315.pdf/AD_2006-0315] (later revised to R1) to require repetitive special detailed inspections (SDI) [rotating probe inspection for cracking] on the horizontal flange of the keel beam in the area of first fastener hole aft of Frame (FR) 40 in order to maintain the structural integrity of the aeroplane. After that [EASA] AD was issued, EASA issued AD 2010–0024 [which corresponds to FAA AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011)], retaining the inspection requirements of EASA AD 2006–0315R1 [http://ad.easa.europa.eu/blob/ easa_ad_2006_0315R1.pdf/AD_20060315R1], which was superseded, extending the applicability to aeroplanes with Airbus Mod 49202 embodied, and reducing the inspection thresholds and intervals. Since that [EASA] AD [2010–0024] was issued, a new fatigue and damage tolerance evaluation has been conducted by Airbus, which concluded that due to the aeroplane utilization, the current inspection threshold and intervals have to be modified. In addition, it was determined that the rototest inspection of fastener hole Nr 6, necessary to ensure that no crack was left unrepaired at the time of fastener hold cold working, was inadvertently not included in Revisions 01 and 02 of both Airbus Service Bulletin (SB) A330–57–3098 and A340–57– 4106. Prompted by these findings, EASA issued AD 2014–0010 [http://ad.easa.europa.eu/ blob/easa_ad_2014-0010.pdf/AD_2014-0010], retaining the requirements of EASA AD 2010–0024, which was superseded, and redefined the inspection thresholds and intervals [by reducing certain compliance times], and added a one-time ultrasonic inspection of fastener hold Nr 6 in the junction keel beam fitting at FR40 on both LH and RH side[s]. Following issuance of EASA AD 2014– 0010, it was identified that there was a need for clarifications [of affected airplanes] * * *. The compliance times vary depending on airplane utilization and configuration. The earliest compliance time for the initial rotating probe inspections is the later of (1) before 10,400 total flight cycles or 67,800 total flight hours, whichever occurs first; and (2) within 24 months or 14,590 flight PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 cycles or 43,790 flight hours, whichever occurs first. The latest compliance time for the initial inspections is the later of (1) before 20,800 total flight cycles or 67,900 total flight hours, whichever occurs first; and (2) within 24 months or 21,180 flight cycles or 63,560 flight hours, whichever occurs first. The compliance times for the repetitive intervals range between 7,800 flight cycles or 50,900 flight hours and 10,700 flight cycles or 35,200 flight hours. The compliance times for the one-time ultrasonic inspection are the latest of (1) 21,000 flight cycles or 60,600 flight hours and within 2,400 flight cycles or 24 months; or the latest of (2) 22,100 flight cycles and 64,400 flight hours, or within 1,300 flight cycles or 24 months. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0937. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Airbus Service Bulletin A330–57– 3081, Revision 05, including Appendix 01, dated November 13, 2012. • Airbus Service Bulletin A330–57– 3090, dated June 15, 2011. • Airbus Service Bulletin A330–57– 3098, dated August 30, 2007. • Airbus Service Bulletin A330–57– 3098, Revision 02, June 15, 2011. • Airbus Service Bulletin A330–57– 3098, Revision 03, including Appendix 01, dated September 24, 2014. • Airbus Service Bulletin A330–57– 3117, including Appendix 01, dated January 25, 2013. • Airbus Service Bulletin A340–57– 4089, Revision 05, including Appendix 01, dated November 13, 2012. • Airbus Service Bulletin A340–57– 4098, Revision 01, dated June 15, 2011. • Airbus Service Bulletin A340–57– 4106, dated August 30, 2007. • Airbus Service Bulletin A340–57– 4106, Revision 02, including Appendix 01, dated August 30, 2007. • Airbus Service Bulletin A340–57– 4106, Revision 03, including Appendix 01, dated September 24, 2012. • Airbus Service Bulletin A340–57– 4126, including Appendix 01, dated January 25, 2013. This service information describes procedures for inspections for cracking of the hole(s) of the horizontal flange of the keel beam, and contacting the manufacturer for repair instructions. Additionally, this service information describes procedures for a one-time ultrasonic inspection for cracking at fastener hole ‘‘Nr 6,’’ and provides E:\FR\FM\04MYP1.SGM 04MYP1 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules optional terminating action for the repetitive inspections. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing widespread fatigue damage (WFD) was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. 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. tkelley on DSK3SPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 35 airplanes of U.S. registry. The actions that are required by AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), and retained in this proposed AD take about 41 work-hours per product, at an average labor rate of $85 per work hour. Required parts cost about $191 per product. Based on these figures, the estimated cost of the actions that are required by AD 2011–24–05 is $3,676 per product. We also estimate that it would take about 23 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $68,425, or $1,955 per product. VerDate Sep<11>2014 17:53 May 01, 2015 Jkt 235001 We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed AD. 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. 25251 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), and adding the following new AD: ■ Airbus: Docket No. FAA–2015–0937; Directorate Identifier 2014–NM–024–AD. (a) Comments Due Date We must receive comments by June 18, 2015. (b) Affected ADs This AD replaces AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011). (c) Applicability (1) This AD applies to the airplanes identified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category, except as provided by paragraph (c)(2) of this AD. (i) Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, all serial numbers, except those on which Airbus modification 55306 or 55792 has been embodied in production. (ii) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes, all serial numbers, except those on which Airbus modification 55306 or 55792 has been embodied in production. (2) This AD does not apply to Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes on which the repair specified in Airbus Repair Drawing R57115053, R57115051, or R57115047 (installation of titanium doubler on both sides) has been accomplished. AD 2007–12– 08, Amendment 39–15086 (72 FR 31171, June 6, 2007), applies to these airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. The Proposed Amendment (e) Reason This AD was prompted by reports of cracks on the keel beam fitting and the front spar of the center wing box. This AD was also prompted by a determination that the rototest inspection and applicable corrective actions of fastener hole Nr 6 were inadvertently omitted from the requirements in AD 2011– 24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011). We are issuing this AD to detect and correct cracking of the fastener holes, which could result in rupture of the keel beam, and consequent reduced structural integrity of the airplane. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (f) Compliance Comply with this AD within the compliance times specified, unless already done. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\04MYP1.SGM 04MYP1 tkelley on DSK3SPTVN1PROD with PROPOSALS 25252 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules (g) Retained Non-Destructive Test (NDT) Inspection This paragraph restates the requirements of paragraph (n) of AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), with new service information and revised credit for certain actions. At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do an NDT inspection of the hole(s) of the horizontal flange of the keel beam located on frame (FR) 40 datum on the right-hand (RH) and/or lefthand (LH) side of the fuselage, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD. Accomplishing an inspection required by paragraph (j) of this AD terminates the inspections required by this paragraph. (1) For airplanes on which an inspection required by paragraph (h) of AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), has not been done as of January 3, 2012 (the effective date of AD 2011–24–05): At the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) For all airplanes except those identified in paragraph (g)(1)(ii) of this AD: Within the ‘‘Mandatory Threshold’’ (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of the Accomplishment Instructions of Airbus Service Bulletin A330–57–3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A340–57–4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011)); whichever occurs later. The compliance times for configurations 02 through 06 specified in the ‘‘Mandatory Threshold’’ column in table 1 of paragraph 1.E., ‘‘Compliance,’’ are total flight cycles and total flight hours. (ii) For Model A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes, except those on which Airbus modification 49202 has been embodied in production, or Airbus Service Bulletin A330–57–3090 has been embodied in service, and Model A340–200 and –300 series airplanes, except those on which Airbus modification 49202 has been embodied in production or Airbus Service Bulletin A340–57–4098 has been embodied in service, and except Model A340–211, –212, –213, –311, –312, and –313 airplanes on which the repair specified in Airbus Repair Drawing R57115053, R57115051, or R57115047 has been accomplished: At the earlier of the times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. (A) Within the ‘‘Mandatory Threshold’’ (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service Bulletin A340–57–4089, including Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330–57–3081, including Appendix 01, Revision 02, dated January 24, 2006; depending on the configuration of the aircraft model; or within 3 months after September 13, 2007, whichever occurs later. The compliance times for Model A330 post-mod. 41652 and VerDate Sep<11>2014 17:53 May 01, 2015 Jkt 235001 pre-mod. 44360, post-mod. 44360, and premod. 49202 (specified in Airbus Service Bulletin A330–57–3081, including Appendix 01, Revision 02, dated January 24, 2006); and Model A340 post-mod. 41652, post-mod. 43500 and pre-mod. 44360, post-mod. 44360 and pre-mod. 49202, and weight variant 027 (specified in Airbus Service Bulletin A340– 57–4089, including Appendix 01, Revision 02, dated January 24, 2006); specified in the ‘‘Mandatory Threshold’’ column in table 1 of paragraph 1.E., ‘‘Compliance,’’ are total flight cycles and total flight hours. (B) Within the ‘‘Mandatory Threshold’’ (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of the Accomplishment Instructions of Airbus Service Bulletin A330–57–3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A340–57– 4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date of AD 2011–24–05, Amendment 39– 16869 (76 FR 73496, November 29, 2011)); whichever occurs later. The compliance times for configurations 02 through 06 specified in the ‘‘Mandatory Threshold’’ column in table 1 of paragraph 1.E., ‘‘Compliance,’’ are total flight cycles and total flight hours. (2) For airplanes on which an inspection required by paragraph (h) of AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), has been done as of January 3, 2012 (the effective date of AD 2011–24–05): At the earlier of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within the ‘‘Mandatory Intervals’’ given in table 1 of paragraph 1.E.(2) of Airbus Service Bulletin A340–57–4089, including Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330–57– 3081, including Appendix 01, Revision 02, dated January 24, 2006; as applicable. (ii) Within the applicable ‘‘Mandatory Interval’’ specified in table 1 of Paragraph 1.E.(2). of Airbus Service Bulletin A330–57– 3081, including Appendix 01, Revision 04, dated May 31, 2011,; or Airbus Service Bulletin A340–57–4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date of AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011)); whichever occurs later. (3) Airbus Service Bulletin A330–57–3081, including Appendix 01, Revision 04, dated May 31, 2011. (4) Airbus Service Bulletin A330–57–3081, including Appendix 01, Revision 05, dated November 13, 2012. (5) Airbus Service Bulletin A340–57–4089, including Appendix 01, Revision 04, dated May 31, 2011. (6) Airbus Service Bulletin A340–57–4089, Revision 05, including Appendix 01, dated November 13, 2012. (h) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (p) of AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011). If no cracking is found during any inspection required by paragraph PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 (g) of this AD, do the actions required by paragraphs (h)(1) and (h)(2) of this AD. (1) Before further flight: Install a new or oversized fastener, as applicable; seal the fastener; and do all other applicable actions; in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD. (2) Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed the ‘‘Mandatory Intervals’’ specified in Paragraph 1.E.(2). of Airbus Service Bulletin A330–57–3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A340–57–4089, including Appendix 01, Revision 04, dated May 31, 2014; as applicable. (i) Retained Corrective Action and Optional Modification (1) This paragraph restates the requirements of paragraph (o) of AD 2011– 24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), with revised method of compliance language. If any cracking is found during any inspection required by paragraph (g) of this AD, 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) This paragraph restates the requirements of paragraph (r) of AD 2011– 24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), with new service information and revised method of compliance language. Modifying the fastener installation in the junction keel beam fitting at FR 40, as specified in paragraph (i)(2)(i), (i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as applicable, terminates the requirements of paragraphs (g) and (h) of this AD; except, for airplanes on which a crack was detected at hole 5 before oversizing of the keel beam, in accordance with step 3.B.(1)(b)3 of the Accomplishment Instructions of Airbus Service Bulletin A330–57–3098, dated August 30, 2007; or Airbus Service Bulletin A340–57–4106, dated August 30, 2007; or in accordance with step 3.C.(2)(c) of the Accomplishment Instructions of Airbus Service Bulletin A330–57–3098, Revision 03, including Appendix 01, dated September 24, 2012, or Airbus Service Bulletin A340–57– 4106, Revision 03, including Appendix 01, dated September 24, 2012; 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 DOA. In case of any crack finding during any modification specified in this paragraph: Where the service information specifies to contact Airbus, 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 DOA. (i) Modification in accordance with Airbus Service Bulletin A330–57–3098, dated August 30, 2007, before January 3, 2012 (the effective date of AD 2011–24–05, E:\FR\FM\04MYP1.SGM 04MYP1 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules tkelley on DSK3SPTVN1PROD with PROPOSALS Amendment 39–16869 (76 FR 73496, November 29, 2011)). (ii) Modification in accordance with Airbus Service Bulletin A330–57–3098, Revision 03, including Appendix 01, dated September 24, 2012, before the effective date of this AD. (iii) Modification in accordance with Airbus Service Bulletin A340–57–4106, dated August 30, 2007, before January 3, 2012 (the effective date of AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011)). (iv) Modification in accordance with Airbus Service Bulletin A340–57–4106, Revision 03, including Appendix 01, dated September 24, 2012, before the effective date of this AD. (j) New Repetitive Rotating Probe Inspections At the applicable times specified in paragraphs (j)(1) and (j)(2) of this AD: Do a rotating probe inspection for cracking of the fastener hole(s) of the horizontal flange of the keel beam located on FR 40 datum on the RH and LH side of the fuselage, as applicable to airplane type and depending on airplane configuration and utilization, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340–57–4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. Repeat the inspection thereafter at intervals not to exceed the ‘‘Mandatory Intervals’’ specified in Paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330–57–3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340–57–4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (1) For airplanes on which the inspection required by paragraph (g) of this AD has not been done as of the effective date of this AD: Do the inspection before exceeding the applicable compliance times specified in the ‘‘mandatory threshold’’ column of the tables in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330– 57–3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340–57–4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable; or within 12 months after the effective date of this AD; whichever occurs later. (2) For airplanes on which the inspection required by paragraph (g) of this AD has been done as of the effective date of this AD: Do the inspection within the applicable compliance times specified in the ‘‘mandatory interval’’ column of the tables in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330– 57–3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340–57–4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable; or within 12 months after the effective date of this AD; whichever occurs later. VerDate Sep<11>2014 17:53 May 01, 2015 Jkt 235001 (k) Credit for Previous Actions (1) This paragraph provides credit for the initial rotating probe inspection that is part of the inspections required by paragraphs (g) and (j)(1) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this AD. (i) Airbus Technical Disposition F57D03012810, Issue B, dated August 18, 2003. (ii) Airbus Technical Disposition 582.0651/ 2002, Issue A, dated October 17, 2002. (2) This paragraph restates the credit for the actions specified in paragraph (k) of AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), if those actions were performed before January 3, 2012 (the effective date of AD 2011–24–05), using the service information specified in paragraphs (k)(2)(i) through (k)(2)(viii) of this AD. (i) Airbus Service Bulletin A330–57–3081, dated October 30, 2003. (ii) Airbus Service Bulletin A330–57–3081, Revision 01, dated May 18, 2004. (iii) Airbus Service Bulletin A330–57– 3081, Revision 02, including Appendix 01, dated January 24, 2006. (iv) Airbus Mandatory Service Bulletin A330–57–3081, Revision 03, dated July 31, 2009. (v) Airbus Service Bulletin A340–57–4089, dated October 30, 2003. (vi) Airbus Service Bulletin A340–57– 4089, Revision 01, dated March 2, 2004. (vii) Airbus Service Bulletin A340–57– 4089, Revision 02, including Appendix 01, dated January 24, 2006. (viii) Airbus Mandatory Service Bulletin A340–57–4089, Revision 03, dated July 31, 2009. (l) New One-Time Ultrasonic Inspection For airplanes in Configuration 2, as defined in the applicable service information identified in paragraph (l)(3), (l)(4), (l)(5), or (l)(6) of this AD, on which the modification has been done as of the effective date of this AD in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (l)(3), (l)(4), (l)(5), or (l)(6) of this AD; as applicable to airplane type; and on which fastener hole ‘‘Nr 5’’ has been bushed before embodiment of Airbus Service Bulletin A330–57–3098, or Airbus Service Bulletin A340–57–4106, as applicable; or on which a crack has been found on fastener hole ‘‘Nr 5’’ during embodiment of Airbus Service Bulletin A330–57–3098, or Airbus Service Bulletin A340–57–4106, as applicable: At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD, do a one-time ultrasonic inspection for cracking at fastener hole ‘‘Nr 6’’ in the junction keel beam fitting at FR 40 LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3117, including Appendix 01, dated January 25, 2013; or Airbus Service Bulletin A340–57–4126, including Appendix 01, dated January 25, 2013; as applicable. (1) For Model A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes: At the later of the times specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 25253 (i) At the applicable time specified in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330– 57–3117, including Appendix 01, dated January 25, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (2) For Model A340–211, –212, –213, –311, –312, and –313 airplanes: At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD. (i) At the applicable time specified in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A340– 57–4126, including Appendix 01, dated January 25, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (3) Airbus Service Bulletin A330–57–3098, Revision 01, dated July 31, 2009. (4) Airbus Service Bulletin A330–57–3098, Revision 02, dated June 15, 2011. (5) Airbus Service Bulletin A340–57–4106, Revision 01, dated July 31, 2009. (6) Airbus Service Bulletin A340–57–4106, Revision 02, dated June 15, 2011. (m) Corrective Actions (1) If no cracking is found during any inspection required by paragraph (j) of this AD, before further flight: Install new or oversized fastener, as applicable; seal the fastener; and do all other applicable corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340–57– 4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. Thereafter, repeat the inspection required by paragraph (j) of this AD at intervals not to exceed the ‘‘Mandatory Intervals’’ specified in Paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330– 57–3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340–57–4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. (2) If any crack is found during any inspection required by paragraph (j) or (l) of this AD; 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 DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (n) Airplanes Excluded From Certain Requirements (1) For airplanes on which a rototest was done at fastener hole Nr 6 before cold working of the fastener hole during accomplishment of the actions specified in the applicable service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: The ultrasonic inspection specified in paragraph (l) of this AD is not required. (i) Airbus Service Bulletin A330–57–3098, Revision 01, dated July 31, 2009. (ii) Airbus Service Bulletin A330–57–3098, Revision 02, dated June 15, 2011. E:\FR\FM\04MYP1.SGM 04MYP1 25254 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules (iii) Airbus Service Bulletin A340–57– 4106, Revision 01, dated June 31, 2009. (iv) Airbus Service Bulletin A340–57– 4106, Revision 02, dated June 15, 2011. (2) For airplanes that have been modified as of the effective date of this AD in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: No action is required by this paragraph, except as otherwise required by paragraph (l) of this AD and, provided that if any crack was found during any modification specified in this paragraph and the service information specified to contact Airbus, repair was done before further flight using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. tkelley on DSK3SPTVN1PROD with PROPOSALS (o) Optional Terminating Actions (1) Modification of an airplane in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (o)(1)(i), (o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or (o)(1)(vi) of this AD; as applicable to airplane type and depending on airplane configuration; terminates the requirements of this AD, provided that in case of any crack finding during any modification specified in this paragraph, and the service information specifies to contact Airbus, repair is done before further flight, using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature (i) Airbus Service Bulletin A330–57–3090, dated March 27, 2006. (ii) Airbus Service Bulletin A330–57–3090, Revision 01, dated June 15, 2011. (iii) Airbus Service Bulletin A330–57– 3098, Revision 03, including Appendix 01, dated September 24, 2012. (iv) Airbus Service Bulletin A340–57– 4098, dated March 27, 2006. (v) Airbus Service Bulletin A340–57–4098, Revision 01, dated June 15, 2011. (vi) Airbus Service Bulletin A340–57– 4106, Revision 03, including Appendix 01, dated September 24, 2012. (2) Accomplishment of the ultrasonic inspection required by paragraph (l) of this AD and all applicable corrective actions required by paragraph (m) of this AD terminates the requirements of this AD for those airplanes. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly VerDate Sep<11>2014 17:53 May 01, 2015 Jkt 235001 to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) AMOCs approved previously for AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), are approved as AMOCs for the corresponding provisions of this AD. (3) 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 DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0010R1, dated May 5, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2015–0937. (2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on April 13, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–10177 Filed 5–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0934; Directorate Identifier 2014–NM–030–AD] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Notice of proposed rulemaking (NPRM). ACTION: We propose to adopt a new airworthiness directive (AD) for all Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE–FALCON 200 airplanes; and Model MYSTERE–FALCON 20–C5, 20– D5, 20–E5, and 20–F5 airplanes. This proposed AD was prompted by reports of defective fire extinguisher tubes. It was determined the defects were caused by corrosion. This proposed AD would require repetitive general visual inspections of the fire extinguisher tubes for cracking and corrosion, and replacement of any cracked tube with a serviceable tube, if necessary. We are proposing this AD to detect and correct cracking and corrosion in the fire extinguisher tubes, which could impact the capability to extinguish an engine fire, and possibly result in damage to the airplane and injury to the passengers. DATES: We must receive comments on this proposed AD by June 18, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0934; 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 Operations 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: Tom Rodriguez, Aerospace Engineer, E:\FR\FM\04MYP1.SGM 04MYP1

Agencies

[Federal Register Volume 80, Number 85 (Monday, May 4, 2015)]
[Proposed Rules]
[Pages 25249-25254]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10177]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-024-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) 2011-24-
05, for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model 
A340-200 and -300 series airplanes. AD 2011-24-05 currently requires 
repetitive inspections for cracking of the hole(s) of the horizontal 
flange of the keel beam, and repair if necessary. Since we issued AD 
2011-24-05, a determination was made that the rototest inspection and 
applicable corrective actions of a certain fastener hole were 
inadvertently omitted from the requirements in that AD. This proposed 
AD would change the inspection compliance times, and, for certain 
airplanes, would add a one-time ultrasonic inspection for cracking at a 
certain fastener hole. This proposed AD would also provide optional 
terminating action for the repetitive inspections. We are proposing 
this AD to detect and correct cracking of the fastener holes, which 
could result in rupture of the keel beam, and consequent reduced 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 18, 2015.

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--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@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://

[[Page 25250]]

www.regulations.gov by searching for and locating Docket No. FAA-2015-
0937; 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 
Operations 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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-2015-0937; 
Directorate Identifier 2014-NM-024-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 November 7, 2011, we issued AD 2011-24-05, Amendment 39-16869 
(76 FR 73496, November 29, 2011), for certain Airbus Model A330-201, -
202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-200 and -300 series airplanes. AD 
2011-24-05 requires actions intended to address the unsafe condition on 
the products listed above.
    Since we issued AD 2011-24-05, Amendment 39-16869 (76 FR 73496, 
November 29, 2011), the European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Union, has 
issued EASA Airworthiness Directive 2014-0010R1, dated May 5, 2014 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-
200 and -300 series airplanes. The MCAI states:

    During A330 and A340 aeroplanes fatigue tests, cracks were 
detected on the RH [right-hand] and LH [left-hand] sides between the 
crossing area of the keel beam fitting and the front spar of the 
Centre Wing Box (CWB).
    This condition, if not detected and corrected, could lead to 
keel beam rupture which would affect the area structural integrity 
of the area.
    Prompted by this potential unsafe condition, EASA issued AD 
2006-0315 [http://ad.easa.europa.eu/blob/easa_ad_2006_0315.pdf/AD_2006-0315] (later revised to R1) to require repetitive special 
detailed inspections (SDI) [rotating probe inspection for cracking] 
on the horizontal flange of the keel beam in the area of first 
fastener hole aft of Frame (FR) 40 in order to maintain the 
structural integrity of the aeroplane.
    After that [EASA] AD was issued, EASA issued AD 2010-0024 [which 
corresponds to FAA AD 2011-24-05, Amendment 39-16869 (76 FR 73496, 
November 29, 2011)], retaining the inspection requirements of EASA 
AD 2006-0315R1 [http://ad.easa.europa.eu/blob/easa_ad_2006_0315R1.pdf/AD_2006-0315R1], which was superseded, 
extending the applicability to aeroplanes with Airbus Mod 49202 
embodied, and reducing the inspection thresholds and intervals.
    Since that [EASA] AD [2010-0024] was issued, a new fatigue and 
damage tolerance evaluation has been conducted by Airbus, which 
concluded that due to the aeroplane utilization, the current 
inspection threshold and intervals have to be modified.
    In addition, it was determined that the rototest inspection of 
fastener hole Nr 6, necessary to ensure that no crack was left 
unrepaired at the time of fastener hold cold working, was 
inadvertently not included in Revisions 01 and 02 of both Airbus 
Service Bulletin (SB) A330-57-3098 and A340-57-4106.
    Prompted by these findings, EASA issued AD 2014-0010 [http://ad.easa.europa.eu/blob/easa_ad_2014-0010.pdf/AD_2014-0010], 
retaining the requirements of EASA AD 2010-0024, which was 
superseded, and redefined the inspection thresholds and intervals 
[by reducing certain compliance times], and added a one-time 
ultrasonic inspection of fastener hold Nr 6 in the junction keel 
beam fitting at FR40 on both LH and RH side[s].
    Following issuance of EASA AD 2014-0010, it was identified that 
there was a need for clarifications [of affected airplanes] * * *.

    The compliance times vary depending on airplane utilization and 
configuration. The earliest compliance time for the initial rotating 
probe inspections is the later of (1) before 10,400 total flight cycles 
or 67,800 total flight hours, whichever occurs first; and (2) within 24 
months or 14,590 flight cycles or 43,790 flight hours, whichever occurs 
first. The latest compliance time for the initial inspections is the 
later of (1) before 20,800 total flight cycles or 67,900 total flight 
hours, whichever occurs first; and (2) within 24 months or 21,180 
flight cycles or 63,560 flight hours, whichever occurs first. The 
compliance times for the repetitive intervals range between 7,800 
flight cycles or 50,900 flight hours and 10,700 flight cycles or 35,200 
flight hours. The compliance times for the one-time ultrasonic 
inspection are the latest of (1) 21,000 flight cycles or 60,600 flight 
hours and within 2,400 flight cycles or 24 months; or the latest of (2) 
22,100 flight cycles and 64,400 flight hours, or within 1,300 flight 
cycles or 24 months.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0937.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A330-57-3081, Revision 05, 
including Appendix 01, dated November 13, 2012.
     Airbus Service Bulletin A330-57-3090, dated June 15, 2011.
     Airbus Service Bulletin A330-57-3098, dated August 30, 
2007.
     Airbus Service Bulletin A330-57-3098, Revision 02, June 
15, 2011.
     Airbus Service Bulletin A330-57-3098, Revision 03, 
including Appendix 01, dated September 24, 2014.
     Airbus Service Bulletin A330-57-3117, including Appendix 
01, dated January 25, 2013.
     Airbus Service Bulletin A340-57-4089, Revision 05, 
including Appendix 01, dated November 13, 2012.
     Airbus Service Bulletin A340-57-4098, Revision 01, dated 
June 15, 2011.
     Airbus Service Bulletin A340-57-4106, dated August 30, 
2007.
     Airbus Service Bulletin A340-57-4106, Revision 02, 
including Appendix 01, dated August 30, 2007.
     Airbus Service Bulletin A340-57-4106, Revision 03, 
including Appendix 01, dated September 24, 2012.
     Airbus Service Bulletin A340-57-4126, including Appendix 
01, dated January 25, 2013.
    This service information describes procedures for inspections for 
cracking of the hole(s) of the horizontal flange of the keel beam, and 
contacting the manufacturer for repair instructions. Additionally, this 
service information describes procedures for a one-time ultrasonic 
inspection for cracking at fastener hole ``Nr 6,'' and provides

[[Page 25251]]

optional terminating action for the repetitive inspections.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this NPRM.

Explanation of Compliance Time

    The compliance time for the modification specified in this proposed 
AD for addressing widespread fatigue damage (WFD) was established to 
ensure that discrepant structure is modified before WFD develops in 
airplanes. Standard inspection techniques cannot be relied on to detect 
WFD before it becomes a hazard to flight. We will not grant any 
extensions of the compliance time to complete any AD-mandated service 
bulletin related to WFD without extensive new data that would 
substantiate and clearly warrant such an extension.

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.

Costs of Compliance

    We estimate that this proposed AD affects 35 airplanes of U.S. 
registry.
    The actions that are required by AD 2011-24-05, Amendment 39-16869 
(76 FR 73496, November 29, 2011), and retained in this proposed AD take 
about 41 work-hours per product, at an average labor rate of $85 per 
work hour. Required parts cost about $191 per product. Based on these 
figures, the estimated cost of the actions that are required by AD 
2011-24-05 is $3,676 per product.
    We also estimate that it would take about 23 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $68,425, or $1,955 
per product.
    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this proposed 
AD.

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:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-
024-AD.

(a) Comments Due Date

    We must receive comments by June 18, 2015.

(b) Affected ADs

    This AD replaces AD 2011-24-05, Amendment 39-16869 (76 FR 73496, 
November 29, 2011).

(c) Applicability

    (1) This AD applies to the airplanes identified in paragraphs 
(c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category, 
except as provided by paragraph (c)(2) of this AD.
    (i) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all serial 
numbers, except those on which Airbus modification 55306 or 55792 
has been embodied in production.
    (ii) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes, all serial numbers, except those on which Airbus 
modification 55306 or 55792 has been embodied in production.
    (2) This AD does not apply to Airbus Model A340-211, -212, -213, 
-311, -312, and -313 airplanes on which the repair specified in 
Airbus Repair Drawing R57115053, R57115051, or R57115047 
(installation of titanium doubler on both sides) has been 
accomplished. AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June 
6, 2007), applies to these airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracks on the keel beam 
fitting and the front spar of the center wing box. This AD was also 
prompted by a determination that the rototest inspection and 
applicable corrective actions of fastener hole Nr 6 were 
inadvertently omitted from the requirements in AD 2011-24-05, 
Amendment 39-16869 (76 FR 73496, November 29, 2011). We are issuing 
this AD to detect and correct cracking of the fastener holes, which 
could result in rupture of the keel beam, and consequent reduced 
structural integrity of the airplane.

(f) Compliance

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

[[Page 25252]]

(g) Retained Non-Destructive Test (NDT) Inspection

    This paragraph restates the requirements of paragraph (n) of AD 
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), 
with new service information and revised credit for certain actions. 
At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do 
an NDT inspection of the hole(s) of the horizontal flange of the 
keel beam located on frame (FR) 40 datum on the right-hand (RH) and/
or left-hand (LH) side of the fuselage, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD. 
Accomplishing an inspection required by paragraph (j) of this AD 
terminates the inspections required by this paragraph.
    (1) For airplanes on which an inspection required by paragraph 
(h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 
2011), has not been done as of January 3, 2012 (the effective date 
of AD 2011-24-05): At the applicable time specified in paragraph 
(g)(1)(i) or (g)(1)(ii) of this AD.
    (i) For all airplanes except those identified in paragraph 
(g)(1)(ii) of this AD: Within the ``Mandatory Threshold'' (flight 
cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of 
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3081, including Appendix 01, Revision 04, dated May 31, 2011; or 
Airbus Service Bulletin A340-57-4089, including Appendix 01, 
Revision 04, dated May 31, 2011; as applicable; or within 3 months 
after January 3, 2012 (the effective date AD 2011-24-05, Amendment 
39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later. 
The compliance times for configurations 02 through 06 specified in 
the ``Mandatory Threshold'' column in table 1 of paragraph 1.E., 
``Compliance,'' are total flight cycles and total flight hours.
    (ii) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes, except those on which 
Airbus modification 49202 has been embodied in production, or Airbus 
Service Bulletin A330-57-3090 has been embodied in service, and 
Model A340-200 and -300 series airplanes, except those on which 
Airbus modification 49202 has been embodied in production or Airbus 
Service Bulletin A340-57-4098 has been embodied in service, and 
except Model A340-211, -212, -213, -311, -312, and -313 airplanes on 
which the repair specified in Airbus Repair Drawing R57115053, 
R57115051, or R57115047 has been accomplished: At the earlier of the 
times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of 
this AD.
    (A) Within the ``Mandatory Threshold'' (flight cycles or flight 
hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service 
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated 
January 24, 2006; or Airbus Service Bulletin A330-57-3081, including 
Appendix 01, Revision 02, dated January 24, 2006; depending on the 
configuration of the aircraft model; or within 3 months after 
September 13, 2007, whichever occurs later. The compliance times for 
Model A330 post-mod. 41652 and pre-mod. 44360, post-mod. 44360, and 
pre-mod. 49202 (specified in Airbus Service Bulletin A330-57-3081, 
including Appendix 01, Revision 02, dated January 24, 2006); and 
Model A340 post-mod. 41652, post-mod. 43500 and pre-mod. 44360, 
post-mod. 44360 and pre-mod. 49202, and weight variant 027 
(specified in Airbus Service Bulletin A340-57-4089, including 
Appendix 01, Revision 02, dated January 24, 2006); specified in the 
``Mandatory Threshold'' column in table 1 of paragraph 1.E., 
``Compliance,'' are total flight cycles and total flight hours.
    (B) Within the ``Mandatory Threshold'' (flight cycles or flight 
hours) specified in table 1 of paragraph 1.E.(2) of the 
Accomplishment Instructions of Airbus Service Bulletin A330-57-3081, 
including Appendix 01, Revision 04, dated May 31, 2011; or Airbus 
Service Bulletin A340-57-4089, including Appendix 01, Revision 04, 
dated May 31, 2011; as applicable; or within 3 months after January 
3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 
FR 73496, November 29, 2011)); whichever occurs later. The 
compliance times for configurations 02 through 06 specified in the 
``Mandatory Threshold'' column in table 1 of paragraph 1.E., 
``Compliance,'' are total flight cycles and total flight hours.
    (2) For airplanes on which an inspection required by paragraph 
(h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 
2011), has been done as of January 3, 2012 (the effective date of AD 
2011-24-05): At the earlier of the times specified in paragraphs 
(g)(2)(i) and (g)(2)(ii) of this AD.
    (i) Within the ``Mandatory Intervals'' given in table 1 of 
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including 
Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service 
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated 
January 24, 2006; as applicable.
    (ii) Within the applicable ``Mandatory Interval'' specified in 
table 1 of Paragraph 1.E.(2). of Airbus Service Bulletin A330-57-
3081, including Appendix 01, Revision 04, dated May 31, 2011,; or 
Airbus Service Bulletin A340-57-4089, including Appendix 01, 
Revision 04, dated May 31, 2011; as applicable; or within 3 months 
after January 3, 2012 (the effective date of AD 2011-24-05, 
Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever 
occurs later.
    (3) Airbus Service Bulletin A330-57-3081, including Appendix 01, 
Revision 04, dated May 31, 2011.
    (4) Airbus Service Bulletin A330-57-3081, including Appendix 01, 
Revision 05, dated November 13, 2012.
    (5) Airbus Service Bulletin A340-57-4089, including Appendix 01, 
Revision 04, dated May 31, 2011.
    (6) Airbus Service Bulletin A340-57-4089, Revision 05, including 
Appendix 01, dated November 13, 2012.

(h) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (p) of AD 
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). If 
no cracking is found during any inspection required by paragraph (g) 
of this AD, do the actions required by paragraphs (h)(1) and (h)(2) 
of this AD.
    (1) Before further flight: Install a new or oversized fastener, 
as applicable; seal the fastener; and do all other applicable 
actions; in accordance with the Accomplishment Instructions of the 
applicable service information specified in paragraph (g)(3), 
(g)(4), (g)(5), or (g)(6) of this AD.
    (2) Repeat the inspection required by paragraph (g) of this AD 
thereafter at intervals not to exceed the ``Mandatory Intervals'' 
specified in Paragraph 1.E.(2). of Airbus Service Bulletin A330-57-
3081, including Appendix 01, Revision 04, dated May 31, 2011; or 
Airbus Service Bulletin A340-57-4089, including Appendix 01, 
Revision 04, dated May 31, 2014; as applicable.

(i) Retained Corrective Action and Optional Modification

    (1) This paragraph restates the requirements of paragraph (o) of 
AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), 
with revised method of compliance language. If any cracking is found 
during any inspection required by paragraph (g) of this AD, 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) This paragraph restates the requirements of paragraph (r) of 
AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), 
with new service information and revised method of compliance 
language. Modifying the fastener installation in the junction keel 
beam fitting at FR 40, as specified in paragraph (i)(2)(i), 
(i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as applicable, 
terminates the requirements of paragraphs (g) and (h) of this AD; 
except, for airplanes on which a crack was detected at hole 5 before 
oversizing of the keel beam, in accordance with step 3.B.(1)(b)3 of 
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3098, dated August 30, 2007; or Airbus Service Bulletin A340-57-
4106, dated August 30, 2007; or in accordance with step 3.C.(2)(c) 
of the Accomplishment Instructions of Airbus Service Bulletin A330-
57-3098, Revision 03, including Appendix 01, dated September 24, 
2012, or Airbus Service Bulletin A340-57-4106, Revision 03, 
including Appendix 01, dated September 24, 2012; 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 DOA. In case of any crack finding during any 
modification specified in this paragraph: Where the service 
information specifies to contact Airbus, 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 DOA.
    (i) Modification in accordance with Airbus Service Bulletin 
A330-57-3098, dated August 30, 2007, before January 3, 2012 (the 
effective date of AD 2011-24-05,

[[Page 25253]]

Amendment 39-16869 (76 FR 73496, November 29, 2011)).
    (ii) Modification in accordance with Airbus Service Bulletin 
A330-57-3098, Revision 03, including Appendix 01, dated September 
24, 2012, before the effective date of this AD.
    (iii) Modification in accordance with Airbus Service Bulletin 
A340-57-4106, dated August 30, 2007, before January 3, 2012 (the 
effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, 
November 29, 2011)).
    (iv) Modification in accordance with Airbus Service Bulletin 
A340-57-4106, Revision 03, including Appendix 01, dated September 
24, 2012, before the effective date of this AD.

(j) New Repetitive Rotating Probe Inspections

    At the applicable times specified in paragraphs (j)(1) and 
(j)(2) of this AD: Do a rotating probe inspection for cracking of 
the fastener hole(s) of the horizontal flange of the keel beam 
located on FR 40 datum on the RH and LH side of the fuselage, as 
applicable to airplane type and depending on airplane configuration 
and utilization, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-57-3081, Revision 05, including 
Appendix 01, dated November 13, 2012; or Airbus Service Bulletin 
A340-57-4089, Revision 05, including Appendix 01, dated November 13, 
2012; as applicable. Repeat the inspection thereafter at intervals 
not to exceed the ``Mandatory Intervals'' specified in Paragraph 
1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin 
A330-57-3081, Revision 05, including Appendix 01, dated November 13, 
2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 
including Appendix 01, dated November 13, 2012; as applicable. 
Accomplishing an inspection required by this paragraph terminates 
the inspections required by paragraph (g) of this AD.
    (1) For airplanes on which the inspection required by paragraph 
(g) of this AD has not been done as of the effective date of this 
AD: Do the inspection before exceeding the applicable compliance 
times specified in the ``mandatory threshold'' column of the tables 
in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus 
Service Bulletin A330-57-3081, Revision 05, including Appendix 01, 
dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, 
Revision 05, including Appendix 01, dated November 13, 2012; as 
applicable; or within 12 months after the effective date of this AD; 
whichever occurs later.
    (2) For airplanes on which the inspection required by paragraph 
(g) of this AD has been done as of the effective date of this AD: Do 
the inspection within the applicable compliance times specified in 
the ``mandatory interval'' column of the tables in paragraph 
1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin 
A330-57-3081, Revision 05, including Appendix 01, dated November 13, 
2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 
including Appendix 01, dated November 13, 2012; as applicable; or 
within 12 months after the effective date of this AD; whichever 
occurs later.

(k) Credit for Previous Actions

    (1) This paragraph provides credit for the initial rotating 
probe inspection that is part of the inspections required by 
paragraphs (g) and (j)(1) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this 
AD.
    (i) Airbus Technical Disposition F57D03012810, Issue B, dated 
August 18, 2003.
    (ii) Airbus Technical Disposition 582.0651/2002, Issue A, dated 
October 17, 2002.
    (2) This paragraph restates the credit for the actions specified 
in paragraph (k) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, 
November 29, 2011), if those actions were performed before January 
3, 2012 (the effective date of AD 2011-24-05), using the service 
information specified in paragraphs (k)(2)(i) through (k)(2)(viii) 
of this AD.
    (i) Airbus Service Bulletin A330-57-3081, dated October 30, 
2003.
    (ii) Airbus Service Bulletin A330-57-3081, Revision 01, dated 
May 18, 2004.
    (iii) Airbus Service Bulletin A330-57-3081, Revision 02, 
including Appendix 01, dated January 24, 2006.
    (iv) Airbus Mandatory Service Bulletin A330-57-3081, Revision 
03, dated July 31, 2009.
    (v) Airbus Service Bulletin A340-57-4089, dated October 30, 
2003.
    (vi) Airbus Service Bulletin A340-57-4089, Revision 01, dated 
March 2, 2004.
    (vii) Airbus Service Bulletin A340-57-4089, Revision 02, 
including Appendix 01, dated January 24, 2006.
    (viii) Airbus Mandatory Service Bulletin A340-57-4089, Revision 
03, dated July 31, 2009.

(l) New One-Time Ultrasonic Inspection

    For airplanes in Configuration 2, as defined in the applicable 
service information identified in paragraph (l)(3), (l)(4), (l)(5), 
or (l)(6) of this AD, on which the modification has been done as of 
the effective date of this AD in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraph (l)(3), (l)(4), (l)(5), or (l)(6) of this AD; as 
applicable to airplane type; and on which fastener hole ``Nr 5'' has 
been bushed before embodiment of Airbus Service Bulletin A330-57-
3098, or Airbus Service Bulletin A340-57-4106, as applicable; or on 
which a crack has been found on fastener hole ``Nr 5'' during 
embodiment of Airbus Service Bulletin A330-57-3098, or Airbus 
Service Bulletin A340-57-4106, as applicable: At the applicable time 
specified in paragraph (l)(1) or (l)(2) of this AD, do a one-time 
ultrasonic inspection for cracking at fastener hole ``Nr 6'' in the 
junction keel beam fitting at FR 40 LH and RH sides, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-57-3117, including Appendix 01, dated January 25, 2013; or 
Airbus Service Bulletin A340-57-4126, including Appendix 01, dated 
January 25, 2013; as applicable.
    (1) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes: At the later of the times 
specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD.
    (i) At the applicable time specified in paragraph 1.E.(2)., of 
the Accomplishment Timescale of Airbus Service Bulletin A330-57-
3117, including Appendix 01, dated January 25, 2013.
    (ii) Within 2,400 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (2) For Model A340-211, -212, -213, -311, -312, and -313 
airplanes: At the later of the times specified in paragraphs 
(l)(2)(i) and (l)(2)(ii) of this AD.
    (i) At the applicable time specified in paragraph 1.E.(2)., of 
the Accomplishment Timescale of Airbus Service Bulletin A340-57-
4126, including Appendix 01, dated January 25, 2013.
    (ii) Within 1,300 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (3) Airbus Service Bulletin A330-57-3098, Revision 01, dated 
July 31, 2009.
    (4) Airbus Service Bulletin A330-57-3098, Revision 02, dated 
June 15, 2011.
    (5) Airbus Service Bulletin A340-57-4106, Revision 01, dated 
July 31, 2009.
    (6) Airbus Service Bulletin A340-57-4106, Revision 02, dated 
June 15, 2011.

(m) Corrective Actions

    (1) If no cracking is found during any inspection required by 
paragraph (j) of this AD, before further flight: Install new or 
oversized fastener, as applicable; seal the fastener; and do all 
other applicable corrective actions; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-57-3081, 
Revision 05, including Appendix 01, dated November 13, 2012; or 
Airbus Service Bulletin A340-57-4089, Revision 05, including 
Appendix 01, dated November 13, 2012; as applicable. Thereafter, 
repeat the inspection required by paragraph (j) of this AD at 
intervals not to exceed the ``Mandatory Intervals'' specified in 
Paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus 
Service Bulletin A330-57-3081, Revision 05, including Appendix 01, 
dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, 
Revision 05, including Appendix 01, dated November 13, 2012; as 
applicable.
    (2) If any crack is found during any inspection required by 
paragraph (j) or (l) of this AD; 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 DOA. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.

(n) Airplanes Excluded From Certain Requirements

    (1) For airplanes on which a rototest was done at fastener hole 
Nr 6 before cold working of the fastener hole during accomplishment 
of the actions specified in the applicable service information 
identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or 
(n)(1)(iv) of this AD: The ultrasonic inspection specified in 
paragraph (l) of this AD is not required.
    (i) Airbus Service Bulletin A330-57-3098, Revision 01, dated 
July 31, 2009.
    (ii) Airbus Service Bulletin A330-57-3098, Revision 02, dated 
June 15, 2011.

[[Page 25254]]

    (iii) Airbus Service Bulletin A340-57-4106, Revision 01, dated 
June 31, 2009.
    (iv) Airbus Service Bulletin A340-57-4106, Revision 02, dated 
June 15, 2011.
    (2) For airplanes that have been modified as of the effective 
date of this AD in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraph 
(n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: No 
action is required by this paragraph, except as otherwise required 
by paragraph (l) of this AD and, provided that if any crack was 
found during any modification specified in this paragraph and the 
service information specified to contact Airbus, repair was done 
before further flight using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.

(o) Optional Terminating Actions

    (1) Modification of an airplane in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (o)(1)(i), (o)(1)(ii), (o)(1)(iii), 
(o)(1)(iv), (o)(1)(v), or (o)(1)(vi) of this AD; as applicable to 
airplane type and depending on airplane configuration; terminates 
the requirements of this AD, provided that in case of any crack 
finding during any modification specified in this paragraph, and the 
service information specifies to contact Airbus, repair is done 
before further flight, using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature
    (i) Airbus Service Bulletin A330-57-3090, dated March 27, 2006.
    (ii) Airbus Service Bulletin A330-57-3090, Revision 01, dated 
June 15, 2011.
    (iii) Airbus Service Bulletin A330-57-3098, Revision 03, 
including Appendix 01, dated September 24, 2012.
    (iv) Airbus Service Bulletin A340-57-4098, dated March 27, 2006.
    (v) Airbus Service Bulletin A340-57-4098, Revision 01, dated 
June 15, 2011.
    (vi) Airbus Service Bulletin A340-57-4106, Revision 03, 
including Appendix 01, dated September 24, 2012.
    (2) Accomplishment of the ultrasonic inspection required by 
paragraph (l) of this AD and all applicable corrective actions 
required by paragraph (m) of this AD terminates the requirements of 
this AD for those airplanes.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) AMOCs approved previously for AD 2011-24-05, Amendment 39-
16869 (76 FR 73496, November 29, 2011), are approved as AMOCs for 
the corresponding provisions of this AD.
    (3) 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 DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0010R1, dated May 5, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-0937.
    (2) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on April 13, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-10177 Filed 5-1-15; 8:45 am]
 BILLING CODE 4910-13-P