Airworthiness Directives; Airbus Airplanes, 13944-13948 [2014-05436]

Download as PDF 13944 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (i) AMOCs approved previously for AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (ii) AMOCs approved previously for AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), are approved as AMOCs for the corresponding provisions of paragraphs (i), (j), and (k) of this AD. (iii) AMOCs approved previously for AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), are approved as AMOCs for the corresponding provisions of paragraphs (l), (m), (n), and (o) of this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the Design Approval Holder with a State of Design Authority’s design organization approval, as applicable). You are required to ensure the product is airworthy before it is returned to service. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. tkelley on DSK3SPTVN1PROD with PROPOSALS (bb) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2012–0176, dated September 7, 2012, corrected September 20, 2012, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0142. (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. VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 Issued in Renton, Washington, on March 4, 2014. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–05435 Filed 3–11–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0138; Directorate Identifier 2013–NM–020–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) 95–24–04, that applies to all Airbus Model A300 series airplanes; Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). AD 95–24– 04 requires repetitive inspections to detect cracks at the aft spar web of the wings, and repair if necessary. Since we issued AD 95–24–04, we have determined that the inspection threshold and interval must be reduced to allow timely detection of cracks and accomplishment of applicable repairs, because of cracking in the rear spar web of the wings between certain ribs due to fatigue-related high shear stress. This proposed AD would reduce the inspection compliance time and interval, and would expand the applicability to airplanes on which a certain Airbus modification has been embodied in production and to airplanes on which a certain Airbus service bulletin has been embodied in service. We are proposing this AD to detect and correct fatigue-related cracking, which could result in reduced structural integrity of the wing. DATES: We must receive comments on this proposed AD by April 28, 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 SUMMARY: PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 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 Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the MCAI, 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: 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–2014–0138; Directorate Identifier 2013–NM–020–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 E:\FR\FM\12MRP1.SGM 12MRP1 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules substantive verbal contact we receive about this proposed AD. tkelley on DSK3SPTVN1PROD with PROPOSALS Discussion On November 9, 1995, we issued AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995). AD 95–24– 04 required actions intended to address an unsafe condition on all Airbus Model A300 series airplanes; Model A300 B4– 600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). Since we issued AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0013R1, dated February 20, 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: Wing fatigue tests carried out by Airbus revealed cracks on the vertical web of the rear spar between Ribs 1 and 2. Similar cracks in the same area were reportedly found by A300 aeroplane operators. In all cases, the cracks ran from the tip of the build slot to the nearest adjacent bolt hole. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, DGAC ´ ´ [Direction Generale de l’Aviation Civile] France issued * * * [an AD] to require an eddy current inspection of the aft face of the wing rear spar in the area adjacent to the build slot on Left Hand (LH) and Right Hand (RH) wings. Since that [French] AD was issued, a fleet survey and updated fatigue and damage tolerance analysis were performed in order to substantiate the second A300–600 Extended Service Goal (ESG2) exercise. The results of the survey and analysis showed that the inspection threshold and interval must be reduced to allow timely detection of cracks and accomplishment of an applicable corrective action. Prompted by these findings, Airbus issued Airbus Service Bulletin (SB) A300–57–6059 Revision 04. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 1997–375–239(B)R3, which is superseded, but redefines the thresholds and intervals. This [EASA] AD also expands the applicability to aeroplanes on which Airbus modification (mod) 12102 has been embodied in production and to aeroplanes on which Airbus SB A300–57–6063 (Airbus mod 11130) has been embodied in service. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA– 2014–0138. VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 Relevant Service Information Airbus has issued Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. For pre-Airbus Modification 11130 (Airbus Service Bulletin A300–57–6063) airplanes, the compliance times are dependent on airplane configuration and utilization. The initial inspection thresholds described in Airbus Mandatory Service Bulletin A300–57– 6059, Revision 04, dated February 22, 2011, range between 18,000 and 23,300 total flight cycles, and between 29,100 and 46,600 total flight hours. The ‘‘grace period’’ specified in Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, is either 1,000 flight cycles, or 1,600 flight hours, or 2,100 flight hours. The repetitive inspection interval ranges between 4,800 and 6,100 flight cycles, and between 7,700 and 12,300 flight hours. For post-Airbus Modification 11130 (Airbus Service Bulletin A300–57–6063) airplanes or post-Airbus production Modification 12102 airplanes, the compliance times are dependent on airplane configuration and utilization. The initial inspection thresholds described in Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, range between 29,900 and 38,700 total flight cycles, and between 48,400 and 77,500 total flight hours. The ‘‘grace period’’ specified in Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, is either 800 or 1,000 flight cycles, or 1,200 or 1,700 flight hours. The repetitive inspection interval ranges between 5,100 and 6,500 flight cycles, or between 8,200 and 13,100 flight hours. 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. Repair Approvals In many FAA transport ADs, when the service information specifies to PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 13945 contact the manufacturer for further instructions if certain discrepancies are found, we typically include in the AD a requirement to accomplish the action using a method approved by either the FAA or the State of Design Authority (or its delegated agent). We have recently been notified that certain laws in other countries do not allow such delegation of authority, but some countries do recognize design approval organizations. In addition, we have become aware that some U.S. operators have used repair instructions that were previously approved by a State of Design Authority or a Design Approval Holder (DAH) as a method of compliance with this provision in FAA ADs. Frequently, in these cases, the previously approved repair instructions come from the airplane structural repair manual or the DAH repair approval statements that were not specifically developed to address the unsafe condition corrected by the AD. Using repair instructions that were not specifically approved for a particular AD creates the potential for doing repairs that were not developed to address the unsafe condition identified by the MCAI AD, the FAA AD, or the applicable service information, which could result in the unsafe condition not being fully corrected. To prevent the use of repairs that were not specifically developed to correct the unsafe condition, certain requirements of this proposed AD specify that the repair approval specifically refer to the FAA AD. This change is intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we use the phrase ‘‘its delegated agent, or the DAH with State of Design Authority design organization approval, as applicable’’ in this proposed AD to refer to a DAH authorized to approve certain required repairs for this proposed AD. Differences Between This 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 action, paragraphs (k) and (n) of this proposed AD would require that you repair any cracking before further flight. Costs of Compliance We estimate that this proposed AD affects 71 products of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\12MRP1.SGM 12MRP1 13946 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules ESTIMATED COSTS Action Labor cost Parts cost 3 work-hour × $85 per hour = $255 per inspection cycle. 3 work-hour × $85 per hour = $255 per inspection cycle. Inspection [actions retained from AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995)]. Inspection [new proposed action] ......................... Cost per product $0 $255 per inspection cycle. $18,105 per inspection cycle. 0 $255 per inspection cycle. $18,105 per inspection cycle. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Authority for This Rulemaking The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 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. tkelley on DSK3SPTVN1PROD with PROPOSALS 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. VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 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) 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995), and adding the following new AD: ■ Airbus: Docket No. FAA–2014–0138; Directorate Identifier 2013–NM–020–AD. (a) Comments Due Date We must receive comments by April 28, 2014. (b) Affected ADs This AD supersedes AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995). (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 203 airplanes. (2) Airbus Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes (3) Airbus Model A300 B4–605R and B4– 622R airplanes. (4) Airbus Model A300 F4–605R airplanes. (5) Airbus Model A300 C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the inspection compliance time and interval must be reduced to allow timely PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 Cost on U.S. operators detection of cracks and accomplishment of applicable repairs if necessary because of cracking in the rear spar web of the wings between certain ribs due to fatigue-related high shear stress. We are issuing this AD to detect and correct fatigue-related cracking, which could result in reduced structural integrity of the wing. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Inspection of Model A300 B2 Series Airplanes This paragraph restates the requirements of paragraph (a) of AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300 B2 series airplanes: Prior to the accumulation of 18,000 total flight cycles, or within 1,400 flight cycles after December 27, 1995 (the effective date of AD 95–24–04), whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. (h) Retained Inspection of Model A300 B4–103, and B4–2C Series Airplanes This paragraph restates the requirements of paragraph (b) of AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300 B4–103, and B4–2C series airplanes: Prior to the accumulation of 19,000 total flight cycles, or within 1,400 flight cycles after December 27, 1995 (the effective date of AD 95–24–04), whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles. (i) Retained Inspection of Model A300 B4–200 Series Airplanes This paragraph restates the requirements of paragraph (c) of AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300 B4–200 series airplanes: Prior to the accumulation of 17,000 total flight cycles, or within 1,400 flight cycles after December 27, 1995 (the effective date of AD 95–24–04), whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, E:\FR\FM\12MRP1.SGM 12MRP1 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. tkelley on DSK3SPTVN1PROD with PROPOSALS (j) Retained Inspection of Model A300–600 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, and F4–605R Series Airplanes This paragraph restates the requirements of paragraph (d) of AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300–600 B4– 601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, and F4–605R series airplanes: Prior to the accumulation of 21,600 flight cycles, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300–57–6059, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. Accomplishment of the initial inspection required by paragraph (l) of this AD terminates the requirements of this paragraph. (k) Retained Repairs This paragraph restates the requirements of paragraph (e) of AD 95–24–04, Amendment 39–9436 (60 FR 58213, November 27, 1995), with new actions. (1) Before the effective date of this AD, if any crack is detected during any inspection required by paragraphs (g) though (j) of this AD: Prior to further flight, repair the crack, in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994; or Airbus Service Bulletin A300–57–6059, dated August 12, 1994; as applicable; or in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. (2) As of the effective date of this AD, if any crack is detected during any inspection required by paragraphs (g) though (j) of this AD: Before further flight, repair the crack, in accordance with Airbus Service Bulletin A300–57–0213, dated August 12, 1994 (for Model A300 B2 series airplanes, and Model A300 B4–103 and B4–2C series airplanes); or Airbus Mandatory Service Bulletin A300–57– 6059, Revision 04, dated February 22, 2011 (for Model A300–600 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, and F4– 605R series airplanes); except if Airbus Service Bulletin A300–57–0213, dated August 12, 1994; or Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011; specifies to contact Airbus for an approved repair, before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder with the EASA design organization approval, as applicable). For a repair method to be approved, the repair approval must specifically refer to this AD. (l) New Repetitive Inspections For airplanes identified in paragraphs (c)(2) through (c)(5) of this AD: At the later of the compliance times specified in paragraph (l)(1) and (l)(2) of this AD, perform an HFEC inspection to detect cracks of the aft VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 face of the wing rear spar web in the area adjacent to the build slot, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011. Repeat the inspection thereafter at the applicable compliance time specified in Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, except as specified in paragraph (m) of this AD. Accomplishment of the initial inspection required by this paragraph terminates the requirements of paragraph (j) of this AD. (1) At the earlier of the applicable compliance times specified in the ‘‘Threshold Inspection’’ column in table 1 through table 4 of paragraph 1.E., ‘‘Compliance,’’ of Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011. Where Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, specifies ‘‘(FH)’’ and ‘‘(FC)’’ in the ‘‘Threshold Inspection’’ columns, this AD specifies ‘‘total flight hours’’ and ‘‘total flight cycles.’’ (2) At the earlier of the applicable compliance times specified in the ‘‘Grace Period’’ column in table 1 through table 4 of paragraph 1.E., ‘‘Compliance,’’ of Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011. Where Airbus Mandatory Service Bulletin A300–57– 6059, Revision 04, dated February 22, 2011, specifies ‘‘(FH)’’ and ‘‘(FC)’’ in the ‘‘Grace Period’’ columns, this AD specifies ‘‘flight hours’’ and ‘‘flight cycles.’’ Where Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, specifies a grace period, this AD requires compliance within the specified compliance time after the effective date of this AD. (m) Compliance Time Exceptions The repetitive inspection required by paragraph (l) of this AD is to be accomplished at the earlier of the applicable compliance time specified in column ‘‘Repeat Interval’’ of table 1 through table 4 of Airbus Mandatory Service Bulletin A300– 57–6059, Revision 04, dated February 22, 2011. Where Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, specifies ‘‘(FC)’’ and ‘‘(FH)’’ in the ‘‘Repeat Interval’’ columns, this AD specifies ‘‘flight hours’’ and ‘‘flight cycles.’’ (n) New Repair If any crack is detected during any inspection required by paragraph (l) of this AD: Before further flight, repair the crack, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011. Where Airbus Mandatory Service Bulletin A300–57–6059, Revision 04, dated February 22, 2011, specifies to contact Airbus for an approved repair: Before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder with the EASA design organization approval, as applicable). For a repair method PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 13947 to be approved, the repair approval must specifically refer to this AD. Repair of any cracking as required by this paragraph does not terminate the repetitive inspections required by paragraph (l) of this AD. (o) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraphs (j) and (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–57–6059, dated August 12, 1994. (2) This paragraph provides credit for the actions required by paragraphs (j), (k), (l), and (n) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–57–6059, Revision 03, dated October 25, 1999, which is not incorporated by reference in this AD. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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. 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the Design Approval Holder with a State of Design Authority’s design organization approval, as applicable). You are required to ensure the product is airworthy before it is returned to service. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Airworthiness Directive 2013–0013R1, dated February 20, 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–2014–0138. (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 E:\FR\FM\12MRP1.SGM 12MRP1 13948 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 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 February 28, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–05436 Filed 3–11–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2014–0104; Airspace Docket No. 13–AEA–4] RIN 2120–AA66 Proposed Amendment and Revocation of Jet Routes; Northeast United States Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to modify segments of jet routes J–64 and J–80, and remove jet route J–77, in the northeastern United States. The FAA is proposing this action because segments of these routes are receiving minimal to no usage due to other more efficient routes in the area. This action would eliminate unneeded route segments, reduce chart clutter and improve chart readability. DATES: Comments must be received on or before April 28, 2014. ADDRESSES: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, M– 30, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001; telephone: (202) 366–9826. You must identify FAA Docket No. FAA–2014–0104 and Airspace Docket No. 13–AEA–4 at the beginning of your comments. You may also submit comments through the Internet at http://www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Paul Gallant, Airspace Policy and Regulations Group, Office of Airspace Services, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 or arguments as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers (FAA Docket No. FAA– 2014–0104 and Airspace Docket No. 13– AEA–4) and be submitted in triplicate to the Docket Management Facility (see ADDRESSES section for address and phone number). You may also submit comments through the Internet at http:// www.regulations.gov. Commenters wishing the FAA to acknowledge receipt of their comments on this action must submit with those comments a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to FAA Docket No. FAA–2014–0104 and Airspace Docket No. 13–AEA–4.’’ The postcard will be date/time stamped and returned to the commenter. All communications received on or before the specified comment closing date will be considered before taking action on the proposed rule. The proposal contained in this action may be changed in light of comments received. All comments submitted will be available for examination in the public docket both before and after the comment closing date. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. Availability of NPRM’s An electronic copy of this document may be downloaded through the Internet at http://www.regulations.gov. You may review the public docket containing the proposal, any comments received and any final disposition in person in the Dockets Office (see ADDRESSES section for address and phone number) between 9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal holidays. An informal docket may also be examined during normal business hours at the office of the Eastern Service Center, Federal Aviation Administration, Room 210, 1701 Columbia Ave., College Park, GA 30337. Persons interested in being placed on a mailing list for future NPRM’s should contact the FAA’s Office of Rulemaking, (202) 267–9677, for a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 Background On October 20, 2011, the FAA amended part of the high altitude route structure in the northeastern United States to expedite the routing of westbound traffic departing the New York Metropolitan area and to realign high altitude overflight traffic to help reduce delays within New York terminal airspace (76 FR 57902). The new and amended routes from that action have enhanced air traffic flows in the area and have become the routes of primary use. The FAA determined that jet route J–77, and portions of jet routes J–64 and J–80, are receiving minimal usage and have been made essentially redundant by other, more efficient route options available in that area. The Proposal The FAA is proposing an amendment to Title 14, Code of Federal Regulations (14 CFR) part 71 to eliminate portions of jet routes J–64 and J–80 and to remove jet route J–77 in the northeastern United States. The proposed changes would eliminate segments that no longer benefit the efficiency of the National Airspace System, reduce chart clutter and improve readability of the affected Enroute High Altitude charts. The proposed route changes are outlined below. J–64: J–64, currently extending between Los Angeles, CA, and Robbinsville, NJ, would terminate at the intersection of the Ravine, PA, 102°(T)/ 113°(M) radial and the Lancaster, PA, 044°(T)/053°(M) radial. This new termination point would be at the SARAA fix, approximately 65 nautical miles northwest of the current end point Robbinsville, NJ. J–77: J–77, currently extending between Boston, MA, and Westminster, MD, would be removed. Other routes are available for navigation between the Baltimore, MD, area and Boston, MA. J–80: J–80, currently extending between Oakland, CA, and Bangor, ME, would terminate at Bellaire, OH, eliminating the segments between Bellaire and Bangor, ME. RNAV route Q–480 and jet route J–581 provide alternative routing between Bellaire, OH, and Bangor, ME. Where new navigation aid radials are cited in a proposed route description, below, both True and Magnetic degrees are listed. Otherwise, only True degrees are stated. Jet routes are published in paragraph 2004 of FAA Order 7400.9X dated August 7, 2013, and effective September 15, 2013, which is incorporated by reference in 14 CFR 71.1. The jet routes E:\FR\FM\12MRP1.SGM 12MRP1

Agencies

[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Proposed Rules]
[Pages 13944-13948]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-05436]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0138; Directorate Identifier 2013-NM-020-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) 95-24-04, 
that applies to all Airbus Model A300 series airplanes; Model A300 B4-
600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes). AD 95-24-04 requires repetitive inspections to detect 
cracks at the aft spar web of the wings, and repair if necessary. Since 
we issued AD 95-24-04, we have determined that the inspection threshold 
and interval must be reduced to allow timely detection of cracks and 
accomplishment of applicable repairs, because of cracking in the rear 
spar web of the wings between certain ribs due to fatigue-related high 
shear stress. This proposed AD would reduce the inspection compliance 
time and interval, and would expand the applicability to airplanes on 
which a certain Airbus modification has been embodied in production and 
to airplanes on which a certain Airbus service bulletin has been 
embodied in service. We are proposing this AD to detect and correct 
fatigue-related cracking, which could result in reduced structural 
integrity of the wing.

DATES: We must receive comments on this proposed AD by April 28, 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 Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the MCAI, 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: 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-2014-0138; 
Directorate Identifier 2013-NM-020-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

[[Page 13945]]

substantive verbal contact we receive about this proposed AD.

Discussion

    On November 9, 1995, we issued AD 95-24-04, Amendment 39-9436 (60 
FR 58213, November 27, 1995). AD 95-24-04 required actions intended to 
address an unsafe condition on all Airbus Model A300 series airplanes; 
Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model 
A300 C4-605R Variant F airplanes (collectively called Model A300-600 
series airplanes).
    Since we issued AD 95-24-04, Amendment 39-9436 (60 FR 58213, 
November 27, 1995), the European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2013-0013R1, dated February 20, 
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:

    Wing fatigue tests carried out by Airbus revealed cracks on the 
vertical web of the rear spar between Ribs 1 and 2. Similar cracks 
in the same area were reportedly found by A300 aeroplane operators. 
In all cases, the cracks ran from the tip of the build slot to the 
nearest adjacent bolt hole.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an 
AD] to require an eddy current inspection of the aft face of the 
wing rear spar in the area adjacent to the build slot on Left Hand 
(LH) and Right Hand (RH) wings.
    Since that [French] AD was issued, a fleet survey and updated 
fatigue and damage tolerance analysis were performed in order to 
substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. The results of the survey and analysis showed that the 
inspection threshold and interval must be reduced to allow timely 
detection of cracks and accomplishment of an applicable corrective 
action.
    Prompted by these findings, Airbus issued Airbus Service 
Bulletin (SB) A300-57-6059 Revision 04.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 1997-375-239(B)R3, which is 
superseded, but redefines the thresholds and intervals. This [EASA] 
AD also expands the applicability to aeroplanes on which Airbus 
modification (mod) 12102 has been embodied in production and to 
aeroplanes on which Airbus SB A300-57-6063 (Airbus mod 11130) has 
been embodied in service.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2014-0138.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.
    For pre-Airbus Modification 11130 (Airbus Service Bulletin A300-57-
6063) airplanes, the compliance times are dependent on airplane 
configuration and utilization. The initial inspection thresholds 
described in Airbus Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011, range between 18,000 and 23,300 total 
flight cycles, and between 29,100 and 46,600 total flight hours. The 
``grace period'' specified in Airbus Mandatory Service Bulletin A300-
57-6059, Revision 04, dated February 22, 2011, is either 1,000 flight 
cycles, or 1,600 flight hours, or 2,100 flight hours. The repetitive 
inspection interval ranges between 4,800 and 6,100 flight cycles, and 
between 7,700 and 12,300 flight hours.
    For post-Airbus Modification 11130 (Airbus Service Bulletin A300-
57-6063) airplanes or post-Airbus production Modification 12102 
airplanes, the compliance times are dependent on airplane configuration 
and utilization. The initial inspection thresholds described in Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, range between 29,900 and 38,700 total flight cycles, and 
between 48,400 and 77,500 total flight hours. The ``grace period'' 
specified in Airbus Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011, is either 800 or 1,000 flight cycles, or 
1,200 or 1,700 flight hours. The repetitive inspection interval ranges 
between 5,100 and 6,500 flight cycles, or between 8,200 and 13,100 
flight hours.

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.

Repair Approvals

    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing repairs that were not developed to address the 
unsafe condition identified by the MCAI AD, the FAA AD, or the 
applicable service information, which could result in the unsafe 
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, certain requirements of this proposed 
AD specify that the repair approval specifically refer to the FAA AD. 
This change is intended to clarify the method of compliance and to 
provide operators with better visibility of repairs that are 
specifically developed and approved to correct the unsafe condition. In 
addition, we use the phrase ``its delegated agent, or the DAH with 
State of Design Authority design organization approval, as applicable'' 
in this proposed AD to refer to a DAH authorized to approve certain 
required repairs for this proposed AD.

Differences Between This 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 action, 
paragraphs (k) and (n) of this proposed AD would require that you 
repair any cracking before further flight.

Costs of Compliance

    We estimate that this proposed AD affects 71 products of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 13946]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection [actions retained from  3 work-hour x $85              $0  $255 per inspection   $18,105 per
 AD 95-24-04, Amendment 39-9436     per hour = $255 per                cycle.                inspection cycle.
 (60 FR 58213, November 27,         inspection cycle.
 1995)].
Inspection [new proposed action].  3 work-hour x $85               0  $255 per inspection   $18,105 per
                                    per hour = $255 per                cycle.                inspection cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates 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) 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), and 
adding the following new AD:

Airbus: Docket No. FAA-2014-0138; Directorate Identifier 2013-NM-
020-AD.

(a) Comments Due Date

    We must receive comments by April 28, 2014.

(b) Affected ADs

    This AD supersedes AD 95-24-04, Amendment 39-9436 (60 FR 58213, 
November 27, 1995).

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes
    (3) Airbus Model A300 B4-605R and B4-622R airplanes.
    (4) Airbus Model A300 F4-605R airplanes.
    (5) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that the inspection 
compliance time and interval must be reduced to allow timely 
detection of cracks and accomplishment of applicable repairs if 
necessary because of cracking in the rear spar web of the wings 
between certain ribs due to fatigue-related high shear stress. We 
are issuing this AD to detect and correct fatigue-related cracking, 
which could result in reduced structural integrity of the wing.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Inspection of Model A300 B2 Series Airplanes

    This paragraph restates the requirements of paragraph (a) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300 B2 series airplanes: Prior to the 
accumulation of 18,000 total flight cycles, or within 1,400 flight 
cycles after December 27, 1995 (the effective date of AD 95-24-04), 
whichever occurs later, perform a high frequency eddy current (HFEC) 
inspection to detect cracks at the aft spar web of the wings, in 
accordance with Airbus Service Bulletin A300-57-0213, dated August 
12, 1994. Repeat the inspection thereafter at intervals not to 
exceed 5,000 flight cycles.

(h) Retained Inspection of Model A300 B4-103, and B4-2C Series 
Airplanes

    This paragraph restates the requirements of paragraph (b) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300 B4-103, and B4-2C series airplanes: Prior 
to the accumulation of 19,000 total flight cycles, or within 1,400 
flight cycles after December 27, 1995 (the effective date of AD 95-
24-04), whichever occurs later, perform an HFEC inspection to detect 
cracks at the aft spar web of the wings, in accordance with Airbus 
Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the 
inspection thereafter at intervals not to exceed 6,000 flight 
cycles.

(i) Retained Inspection of Model A300 B4-200 Series Airplanes

    This paragraph restates the requirements of paragraph (c) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300 B4-200 series airplanes: Prior to the 
accumulation of 17,000 total flight cycles, or within 1,400 flight 
cycles after December 27, 1995 (the effective date of AD 95-24-04), 
whichever occurs later, perform an HFEC inspection to detect cracks 
at the aft spar web of the wings,

[[Page 13947]]

in accordance with Airbus Service Bulletin A300-57-0213, dated 
August 12, 1994. Repeat the inspection thereafter at intervals not 
to exceed 5,000 flight cycles.

(j) Retained Inspection of Model A300-600 B4-601, B4-603, B4-620, B4-
622, B4-605R, B4-622R, and F4-605R Series Airplanes

    This paragraph restates the requirements of paragraph (d) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
no changes. For Model A300-600 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R series airplanes: Prior to the 
accumulation of 21,600 flight cycles, perform an HFEC inspection to 
detect cracks at the aft spar web of the wings, in accordance with 
Airbus Service Bulletin A300-57-6059, dated August 12, 1994. Repeat 
the inspection thereafter at intervals not to exceed 5,700 flight 
cycles. Accomplishment of the initial inspection required by 
paragraph (l) of this AD terminates the requirements of this 
paragraph.

(k) Retained Repairs

    This paragraph restates the requirements of paragraph (e) of AD 
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with 
new actions.
    (1) Before the effective date of this AD, if any crack is 
detected during any inspection required by paragraphs (g) though (j) 
of this AD: Prior to further flight, repair the crack, in accordance 
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994; or 
Airbus Service Bulletin A300-57-6059, dated August 12, 1994; as 
applicable; or in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA.
    (2) As of the effective date of this AD, if any crack is 
detected during any inspection required by paragraphs (g) though (j) 
of this AD: Before further flight, repair the crack, in accordance 
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994 
(for Model A300 B2 series airplanes, and Model A300 B4-103 and B4-2C 
series airplanes); or Airbus Mandatory Service Bulletin A300-57-
6059, Revision 04, dated February 22, 2011 (for Model A300-600 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R series 
airplanes); except if Airbus Service Bulletin A300-57-0213, dated 
August 12, 1994; or Airbus Mandatory Service Bulletin A300-57-6059, 
Revision 04, dated February 22, 2011; specifies to contact Airbus 
for an approved repair, before further flight, repair the crack 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent, or the Design 
Approval Holder with the EASA design organization approval, as 
applicable). For a repair method to be approved, the repair approval 
must specifically refer to this AD.

(l) New Repetitive Inspections

    For airplanes identified in paragraphs (c)(2) through (c)(5) of 
this AD: At the later of the compliance times specified in paragraph 
(l)(1) and (l)(2) of this AD, perform an HFEC inspection to detect 
cracks of the aft face of the wing rear spar web in the area 
adjacent to the build slot, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-57-6059, 
Revision 04, dated February 22, 2011. Repeat the inspection 
thereafter at the applicable compliance time specified in Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, except as specified in paragraph (m) of this AD. 
Accomplishment of the initial inspection required by this paragraph 
terminates the requirements of paragraph (j) of this AD.
    (1) At the earlier of the applicable compliance times specified 
in the ``Threshold Inspection'' column in table 1 through table 4 of 
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin 
A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, specifies ``(FH)'' and ``(FC)'' in the ``Threshold 
Inspection'' columns, this AD specifies ``total flight hours'' and 
``total flight cycles.''
    (2) At the earlier of the applicable compliance times specified 
in the ``Grace Period'' column in table 1 through table 4 of 
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin 
A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011, specifies ``(FH)'' and ``(FC)'' in the ``Grace Period'' 
columns, this AD specifies ``flight hours'' and ``flight cycles.'' 
Where Airbus Mandatory Service Bulletin A300-57-6059, Revision 04, 
dated February 22, 2011, specifies a grace period, this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.

(m) Compliance Time Exceptions

    The repetitive inspection required by paragraph (l) of this AD 
is to be accomplished at the earlier of the applicable compliance 
time specified in column ``Repeat Interval'' of table 1 through 
table 4 of Airbus Mandatory Service Bulletin A300-57-6059, Revision 
04, dated February 22, 2011. Where Airbus Mandatory Service Bulletin 
A300-57-6059, Revision 04, dated February 22, 2011, specifies 
``(FC)'' and ``(FH)'' in the ``Repeat Interval'' columns, this AD 
specifies ``flight hours'' and ``flight cycles.''

(n) New Repair

    If any crack is detected during any inspection required by 
paragraph (l) of this AD: Before further flight, repair the crack, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February 
22, 2011. Where Airbus Mandatory Service Bulletin A300-57-6059, 
Revision 04, dated February 22, 2011, specifies to contact Airbus 
for an approved repair: Before further flight, repair the crack 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent, or the Design 
Approval Holder with the EASA design organization approval, as 
applicable). For a repair method to be approved, the repair approval 
must specifically refer to this AD. Repair of any cracking as 
required by this paragraph does not terminate the repetitive 
inspections required by paragraph (l) of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (j) and (k) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A300-57-6059, dated August 12, 1994.
    (2) This paragraph provides credit for the actions required by 
paragraphs (j), (k), (l), and (n) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A300-57-6059, Revision 03, dated October 25, 1999, which is 
not incorporated by reference in this AD.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the International Branch, send it 
to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone (425) 227-2125; fax (425) 227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Airworthiness Directive 2013-0013R1, dated February 20, 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-2014-0138.
    (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

[[Page 13948]]

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 February 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-05436 Filed 3-11-14; 8:45 am]
BILLING CODE 4910-13-P