Airworthiness Directives; Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C Airplanes, 26962-26967 [2011-11335]

Download as PDF 26962 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules ´ Aeronautica S.A., Phenom Maintenance Support, Av. Brig. Faria Lima, 2170, Sao Jose dos Campos—SP, CEP: 12227–901—PO Box: 36/2, Brasil; telephone: ++55 12 3927–5383; fax: ++55 12 3927–2619; E-mail: phenom.reliability@embraer.com.br; Internet: https://www.embraer.com.br. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. Issued in Kansas City, Missouri, on May 4, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–11334 Filed 5–9–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0389; Directorate Identifier 2007–NM–189–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2–1C, A300 B2–203, A300 B2K– 3C, A300–B4–103, A300 B4–203, and A300 B4–2C Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: mstockstill on DSKH9S0YB1PROD with PROPOSALS * * * [C]racks * * * in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames 18 and 80 which could affect the structural integrity of the fuselage if not corrected. * * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by June 24, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. VerDate Mar<15>2010 17:24 May 09, 2011 Jkt 223001 • 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 W12–40, 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— EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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 https:// 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 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, Washington 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–2011–0389; Directorate Identifier 2007–NM–189–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 https:// PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 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 December 20, 1989, we issued AD 90–01–10, Amendment 39–6448 (55 FR 261, January 4, 1990). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 90–01–10, Airbus has refined the inspection program for cracking at areas of the fuselage defined in AD 90–01–10 as ‘‘special areas’’ (paragraph A.1. of AD 90–01–10), ‘‘standard areas’’ (paragraph A.2. of AD 90–01–10), and ‘‘modified or repaired areas’’ (paragraph A.3. of AD 90–01–10). The new inspection program is designed to allow airplanes to reach their limit of validity (LOV). Certain compliance times are reduced and certain other compliance times are extended. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2007–0091, dated April 10, 2007, and corrected June 23, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: This Airworthiness Directive (AD) is issued in order to prevent cracks development in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames 18 and 80 which could affect the structural integrity of the fuselage if not corrected. This new AD: —Retains the requirements of DGAC AD 1989–061–092(B)R4 [which corresponds to FAA AD 90–01–10], which is cancelled; —Takes into account a new inspection program as detailed in AIRBUS Service Bulletins (SB) A300–53–0211 Revision 7, which will allow A300 aircraft to reach the Limit of Validity (LOV). This AD has been republished to correctly refer to SB A300–53–0211 in Note 2 of the Compliance section. The inspection program consists of repetitive detailed inspections for disbonding and cracking of the fuselage inner doubler; eddy current and ultrasonic inspections of the fuselage longitudinal lap joints for cracking; and repair if necessary (i.e., repairing any cracking or disbonding, or contacting Airbus for repair instructions and doing the repair). You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletin A300–53–229, Revision 5, dated April 8, E:\FR\FM\10MYP1.SGM 10MYP1 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 1997; and Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the proposed AD. mstockstill on DSKH9S0YB1PROD with PROPOSALS Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 5 products of U.S. registry. We estimate that it would take about 3,735 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,587,375, or $317,475 per product. 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: VerDate Mar<15>2010 17:24 May 09, 2011 Jkt 223001 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); and 3. 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. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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 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 Amendment 39–6448 (55 FR 261, January 4, 1990) and adding the following new AD: Airbus: Docket No. FAA–2011–0389; Directorate Identifier 2007–NM–189–AD. Comments Due Date (a) We must receive comments by June 24, 2011. PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 26963 Affected ADs (b) This AD supersedes AD 90–01–10, Amendment 39–6448. Applicability (c) This AD applies to Airbus Model A300 B2–1C, A300 B2–203, A300 B2K–3C, A300– B4–103, A300 B4–203, and A300 B4–2C airplanes; certificated in any category; serial numbers 0003 through 0156 inclusive. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: This Airworthiness Directive (AD) is issued in order to prevent cracks development in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames 18 and 80 which could affect the structural integrity of the fuselage if not corrected. This new AD: —Retains the requirements of DGAC AD 1989–061–092(B)R4[which corresponds to FAA AD 90–10–10], which is cancelled; —Takes into account a new inspection program as detailed in AIRBUS Service Bulletins (SB) A300–53–0211 Revision 7, which will allow A300 aircraft to reach the Limit of Validity (LOV). This AD has been republished to correctly refer to SB A300–53–0211 in Note 2 of the Compliance section. The inspection program consists of repetitive detailed inspections for disbonding and cracking of the fuselage inner doubler; eddy current and ultrasonic inspections of the fuselage longitudinal lap joints for cracking; and repair if necessary (i.e., repairing any cracking or disbonding, or contacting Airbus for repair instructions and doing the repair). Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections of ‘‘Special Areas’’ and Repair or Modification if Necessary (g) For airplanes on which an eddy current inspection of the ‘‘special’’ areas of the longitudinal lap joints has not been done as of the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300–53–0211: Prior to the accumulation of 24,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later; do an eddy current inspection for cracking of the ‘‘special’’ areas of the longitudinal lap joints, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 1 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53– E:\FR\FM\10MYP1.SGM 10MYP1 26964 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 0211, Revision 07, dated December 1, 2006; and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ‘‘Special’’ areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300–53– 0211, Revision 07, dated December 1, 2006. TABLE 1—REPETITIVE INTERVALS FOR INSPECTING SPECIAL AREAS OF THE LONGITUDINAL LAP JOINTS For airplanes— Inspect special area— Repeat at intervals not to exceed— All ............................................................. All ............................................................. All ............................................................. All ............................................................. MSN 003 .................................................. STGR5 LH and RH (FR54 through FR58) ........... STGR22 LH and RH (FR26 through FR40) ......... STGR22 RH (FR58 through FR65) ...................... STGR31 LH/RH (FR26 through FR39) ................. STGR31 LH/RH (FR54 through FR58) ................. 3,600 2,700 3,000 3,000 3,600 (h) For airplanes on which an eddy current inspection of the ‘‘special’’ areas of the longitudinal lap joints has been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53– 0211; except for airplanes on which a repair or modification of the ‘‘special’’ areas has been done in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211: Do the next inspection of the ‘‘special’’ areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 2 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the repaired or flight flight flight flight flight cycles cycles cycles cycles cycles modified area in accordance with paragraph (k) of this AD. ‘‘Special’’ areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. (1) Within 6,000 flight cycles after doing the last inspection of the ‘‘special’’ areas of the longitudinal lap joints, in accordance with Airbus Mandatory Service Bulletin A300–53–0211. (2) Within the applicable intervals specified in Table 2 of this AD, or within 60 days after the effective date of this AD, whichever occurs later. TABLE 2—REPETITIVE INTERVALS FOR INSPECTING SPECIAL AREAS OF THE LONGITUDINAL LAP JOINTS For airplanes— Inspect special area— Repeat at intervals not to exceed— All ............................................................. All ............................................................. All ............................................................. All ............................................................. MSN 003 .................................................. STGR5 LH and RH (FR54 through FR58) ........... STGR22 LH and RH (FR26 through FR40) ......... STGR22 RH (FR58 through FR65) ...................... STGR31 LH/RH (FR26 through FR39) ................. STGR31 LH/RH (FR54 through FR58) ................. 3,600 2,700 3,000 3,000 3,600 Repetitive Inspections of ‘‘Standard Areas’’ and Repair or Modification If Necessary (i) For airplanes on which an eddy current inspection of the ‘‘standard’’ areas of the longitudinal lap joints has not been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211: At the applicable time specified in Tables 3 and 4 of this AD, do an eddy current inspection for cracking of the longitudinal lap joints in the ‘‘standard’’ areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. Repeat the inspection thereafter at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair flight flight flight flight flight cycles cycles cycles cycles cycles or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53– 0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the applicable area specified in Tables 3 and 4 of this AD. ‘‘Standard’’ areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. TABLE 3—INITIAL COMPLIANCE TIMES AND REPETITIVE INTERVALS FOR INSPECTING STANDARD AREAS OF THE LONGITUDINAL LAP JOINTS Before the accumulation of— Inspect standard area— Repeat at intervals not to exceed— All .............................................. 32,000 total flight cycles ..................... 32,000 total flight cycles ..................... All .............................................. 32,000 total flight cycles ..................... All .............................................. 32,000 total flight cycles ..................... All .............................................. 32,000 total flight cycles ..................... STGR5, 13, 22 LH and RH, STGR31 LH (FR18 through FR26). STGR27 RH, STGR39 RH (FR18 through FR20A, FR25A, FR26). STGR43 LH, STGR46 RH, STGR51 LH (FR19 through FR26). STGR5 LH/RH (FR26 through FR40) STGR11 LH/RH (FR27 through FR32) STGR13 LH/RH (FR 26 through FR28, FR31 through FR40) STGR27 LH/RH (FR 27 through FR32) STGR43 LH/RH (FR 26 through FR39) STGR49 RH (FR26 through FR39). STGR47 LH (FR26 through FR39) .... 3,600 flight cycles All .............................................. mstockstill on DSKH9S0YB1PROD with PROPOSALS For airplanes— VerDate Mar<15>2010 17:24 May 09, 2011 Jkt 223001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 E:\FR\FM\10MYP1.SGM 10MYP1 8,000 flight cycles 5,700 flight cycles 3,000 flight cycles 5,700 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 26965 TABLE 3—INITIAL COMPLIANCE TIMES AND REPETITIVE INTERVALS FOR INSPECTING STANDARD AREAS OF THE LONGITUDINAL LAP JOINTS—Continued For airplanes— Before the accumulation of— All .............................................. 32,000 total flight cycles ..................... All except MSN 0003 ................ 32,000 total flight cycles ..................... STGR5, 13, 22 LH/RH (FR40 FR54). STGR13, 44, 52 LH/RH through FR58) STGR22 (FR54, FR55) STGR31 (FR54 through FR58). Repeat at intervals not to exceed— Inspect standard area— (j) For airplanes on which an eddy current inspection of the ‘‘standard’’ areas of the longitudinal lap joints has been done as of the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53– 0211; except for airplanes on which a repair or modification of the ‘‘standard areas’’ has been done in accordance with Airbus Mandatory Service Bulletin A300–53–0211: Do the next inspection of the ‘‘standard’’ areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. Thereafter, if no cracking is found, repeat the inspection at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify through 5,000 (FR54 LH/RH LH/RH 3,600 before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ‘‘Standard’’ areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. TABLE 4—INITIAL COMPLIANCE TIMES AND REPETITIVE INTERVALS FOR INSPECTING ADDITIONAL STANDARD AREAS OF THE LONGITUDINAL LAP JOINTS Before the accumulation of— Inspect standard area— Repeat at intervals not to exceed— Pre-Mod 1398 ........................... 32,000 total flight cycles ..................... 32,000 total flight cycles ..................... Post-Mod 1398 ......................... 32,000 total flight cycles ..................... Pre-Mod 1398 ........................... 32,000 total flight cycles ..................... Post-Mod 1398 ......................... 32,000 total flight cycles ..................... All .............................................. 32,000 total flight cycles ..................... All .............................................. All .............................................. 24,000 total flight cycles ..................... 32,000 total flight cycles ..................... All .............................................. 32,000 total flight cycles ..................... All .............................................. 27,000 total flight cycles ..................... STGR5, 13 LH/RH 22 LH (FR58 through FR65) STGR31 LH (FR58 through FR72) STGR31 RH (FR65 through FR72). STGR27 RH, STGR39 RH (FR58, FR59A, FR63A through FR65). STGR5, 13 LH/RH 22 LH (FR58 through FR65) STGR31 LH (FR58 through FR72) STGR 31 RH (FR65 through FR72). STGR5, 13, 22 LH/RH (FR65 through FR72). STGR5, 13, 22 LH/RH (FR65 through FR72). STGR44 LH (FR58 through FR72) STGR52 LH/RH (FR58 through FR65) STGR47 RH (FR58 through FR72) STGR57 LH (FR65 through FR72). STGR22 RH (FR58 through FR65) .... STGR6 LH/RH (FR72 through FR80) STGR24 LH/RH (FR76 through FR80). STRG17 LH/RH (FR76 through FR80) STGR29 LH/RH (FR72 through FR76). STGR35 LH/RH (FR72 through FR80). STGR51 LH/RH (FR72 through FR80). 2,700 flight cycles All .............................................. mstockstill on DSKH9S0YB1PROD with PROPOSALS For airplanes— (1) Within the applicable time in paragraph (j)(1)(i) or (j)(1)(ii) of this AD after doing the last inspection of the ‘‘standard’’ areas of the longitudinal lap joints in accordance with Airbus Mandatory Service Bulletin A300–53– 0211. (i) For longitudinal lap joints with bonded doublers: 6,000 flight cycles. (ii) For longitudinal lap joints without bonded doublers: 8,000 flight cycles. VerDate Mar<15>2010 17:24 May 09, 2011 Jkt 223001 (2) Within the applicable time specified in Tables 3 or 4 of this AD, or within 60 days after the effective date of this AD, whichever occurs later. Post-Repair or Modification Inspections and Repair or Modification if Necessary (k) For airplanes on which a repair or modification has been done in accordance with the Accomplishment Instructions of PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 8,000 flight cycles 3,000 flight cycles 2,300 flight cycles 3,000 flight cycles 3,000 flight cycles 3,000 flight cycles 3,000 flight cycles 5,700 flight cycles 5,700 flight cycles Airbus Mandatory Service Bulletin A300–53– 0211: At the applicable initial inspection time specified in Table 5 of this AD, do an eddy current inspection for cracking of the repaired or modified areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53– 0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified E:\FR\FM\10MYP1.SGM 10MYP1 26966 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules in Table 5 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006. TABLE 5—POST-REPAIR OR MODIFICATION COMPLIANCE TIME Repair or retrofit solution/area—as identified in airbus mandatory service bulletin A300–53–0211 Repair 1: (Without cut out) also applicable to the solution with removed inner doubler. Repair 4 (With cut out) ..................................................... Repair 4A (With cut out) ................................................... Repair 7 (MSN 0095 at STGR52 LH in Section 16) ........ Repair 9 (MSN 0073 and 0095 STGR44 LH/RH in Sections 16 and 17). Repair 10 (Post-repair inspections in Figure 13) ............. Repair 2 (With cut out) ..................................................... Repair 3 (Without cut out) ................................................ Retrofit 1 (Retrofit lap joint) .............................................. Retrofit 2 Retrofit lower shell (4 panel solution) STGR43 LH (FR26 through FR39), STGR43 RH (FR26 through FR38), and STGR49 RH (FR26 through FR38). Retrofit 2 Retrofit lower shell (4 panel solution) STGR 46 RH (FR19 through FR26), and STGR47 LH (FR26 through FR39), and STGR51 LH (FR19 through FR26). Retrofit 3 Retrofit lower shell (3 panel solution) STGR43 LH (FR26 through FR39), and STGR43 RH (FR26 through FR38). Retrofit 3 Retrofit lower shell (3 panel solution) STGR46 RH (FR19 through FR26), and STGR51 LH (FR19 through FR26), and STGR 54 LH (FR26 through FR39). Retrofit 3A (STGR43 LH/RH between FR37 and FR39 in Section 14). Retrofit 4 (Retrofit lap joint without cut out) ...................... Retrofit 5 (Retrofit lap joint) .............................................. Retrofit 6 (Retrofit lap joint) .............................................. Retrofit 7 (Retrofit lap joint) .............................................. Fuselage Inner Doubler Inspections and Repair if Necessary (l) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have not been done as of the Initial inspection after repair or retrofit— Follow-up inspections at intervals not to exceed— Skin/doubler thickness .................................................... • < 1 inch: 10,000 flight cycles after repair .................... • ≥ 1 inch and < 2 inch: 30,000 flight cycles after repair • ≥ 2 inch: 60,000 flight cycles after repair .................... Within 32,000 flight cycles after repair ........................... Within 24,000 flight cycles after repair ........................... Within 37,000 flight cycles after repair ........................... Within 36,000 flight cycles after repair ........................... 2,000 flight cycles. 6,400 flight cycles. 5,000 flight cycles. 5,300 flight cycles. 12,000 flight cycles. 5,000 flight cycles. Within Within Within Within Within 11,000 flight cycles. 5,300 flight cycles. 5,300 flight cycles. 5,000 flight cycles. 3,000 flight cycles. 20,000 24,000 24,000 32,000 32,000 flight flight flight flight flight cycles cycles cycles cycles cycles after after after after after repair repair repair retrofit retrofit ........................... ........................... ........................... .......................... .......................... 1,000 flight cycles. Within 32,000 flight cycles after retrofit .......................... 5,700 flight cycles. Within 32,000 flight cycles after retrofit .......................... 3,000 flight cycles. Within 32,000 flight cycles after retrofit .......................... 5,700 flight cycles. Within 32,000 flight cycles after retrofit .......................... 5,000 flight cycles. Within Within Within Within 5,000 flight cycles. 5,000 flight cycles. 12,000 flight cycles. 5,400 flight cycles. 42,000 42,000 34,000 47,600 flight flight flight flight cycles cycles cycles cycles after after after after retrofit retrofit retrofit retrofit effective date of this AD in accordance with Airbus Service Bulletin A300–53–229: Prior to the accumulation of 24,000 total flight cycles or within 15 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through .......................... .......................... .......................... .......................... 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 6 of this AD. TABLE 6—REPETITIVE INTERVALS FOR INSPECTIONS FOR DISBONDING AND CRACKING Inspect at intervals not to exceed— Sections 13 and 14 as specified in Airbus Service Bulletin A300–53–229. Sections 15 through 18 as specified in Airbus Service Bulletin A300–53–229. mstockstill on DSKH9S0YB1PROD with PROPOSALS For area— Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first. Within 8.5 years or 12,000 flight cycles after doing the inspection, whichever occurs first. (1) If no cracking is found and ‘‘minor’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found and ‘‘major’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Within VerDate Mar<15>2010 17:24 May 09, 2011 Jkt 223001 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 (m) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300–53–229; except for airplanes on which a repair of that area has been done in accordance with Airbus Service E:\FR\FM\10MYP1.SGM 10MYP1 mstockstill on DSKH9S0YB1PROD with PROPOSALS Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules Bulletin A300–53–229: At the applicable time specified in Table 6 of this AD, or within 60 days after the effective date of this AD, whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and righthand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection at the applicable intervals specified in Table 6 of this AD. (1) If no cracking is found and ‘‘minor’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found and ‘‘major’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. (n) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have not been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300–53–229: Prior to the accumulation of 24,000 total flight cycles or within 12 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found and ‘‘minor’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found and ‘‘major’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. VerDate Mar<15>2010 17:24 May 09, 2011 Jkt 223001 (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. (o) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300–53–229; except airplanes on which a repair of that area has been done in accordance with Airbus Service Bulletin A300–53–229: Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–229, Revision 5, dated April 8, 1997. If no disbonding and corrosion are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found and ‘‘minor’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found and ‘‘major’’ disbonding, as defined in Airbus Service Bulletin A300–53–229, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997. (p) Although Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997; and Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006; specify to submit certain information to the manufacturer, this AD does not include that requirement. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: (1) Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, this AD requires that you repair the crack(s) before further flight. (2) The MCAI or service information does not include enforceable compliance times for certain actions; however, this AD requires that those actions be done at the enforceable times specified in this AD. (3) Although the MCAI or service information tells you to submit information PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 26967 to the manufacturer, paragraph (p) of this AD specifies that such submittal is not required. Other FAA AD Provisions (q) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed 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 or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Related Information (r) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007–0091, dated April 10, 2007, corrected June 23, 2008; Airbus Service Bulletin A300–53–229, Revision 5, dated April 8, 1997; and Airbus Mandatory Service Bulletin A300–53–0211, Revision 07, dated December 1, 2006; for related information. Issued in Renton, Washington, on April 28, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–11335 Filed 5–9–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE INTERIOR National Indian Gaming Commission 25 CFR Chapter III Regulatory Review Schedule National Indian Gaming Commission. ACTION: Notice of comment periods on preliminary drafts. AGENCY: On November 18, 2010, the National Indian Gaming Commission (NIGC) issued a Notice of Inquiry and SUMMARY: E:\FR\FM\10MYP1.SGM 10MYP1

Agencies

[Federal Register Volume 76, Number 90 (Tuesday, May 10, 2011)]
[Proposed Rules]
[Pages 26962-26967]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-11335]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0389; Directorate Identifier 2007-NM-189-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2-1C, A300 B2-203,
A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
MCAI describes the unsafe condition as:

* * * [C]racks * * * in sections 13 to 18 of the fuselage between
rivets of longitudinal lap joints between frames 18 and 80 which
could affect the structural integrity of the fuselage if not
corrected.

* * * * *
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by June 24, 2011.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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 W12-40, 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--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail: account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. 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 https://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 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, Washington 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-2011-0389;
Directorate Identifier 2007-NM-189-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 https://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 December 20, 1989, we issued AD 90-01-10, Amendment 39-6448 (55
FR 261, January 4, 1990). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 90-01-10, Airbus has refined the inspection
program for cracking at areas of the fuselage defined in AD 90-01-10 as
``special areas'' (paragraph A.1. of AD 90-01-10), ``standard areas''
(paragraph A.2. of AD 90-01-10), and ``modified or repaired areas''
(paragraph A.3. of AD 90-01-10). The new inspection program is designed
to allow airplanes to reach their limit of validity (LOV). Certain
compliance times are reduced and certain other compliance times are
extended.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2007-0091, dated April 10, 2007, and corrected
June 23, 2008 (referred to after this as ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:

This Airworthiness Directive (AD) is issued in order to prevent
cracks development in sections 13 to 18 of the fuselage between
rivets of longitudinal lap joints between frames 18 and 80 which
could affect the structural integrity of the fuselage if not
corrected.
This new AD:
--Retains the requirements of DGAC AD 1989-061-092(B)R4 [which
corresponds to FAA AD 90-01-10], which is cancelled;
--Takes into account a new inspection program as detailed in
AIRBUS Service Bulletins (SB) A300-53-0211 Revision 7, which will
allow A300 aircraft to reach the Limit of Validity (LOV).
This AD has been republished to correctly refer to SB A300-53-
0211 in Note 2 of the Compliance section.

The inspection program consists of repetitive detailed inspections for
disbonding and cracking of the fuselage inner doubler; eddy current and
ultrasonic inspections of the fuselage longitudinal lap joints for
cracking; and repair if necessary (i.e., repairing any cracking or
disbonding, or contacting Airbus for repair instructions and doing the
repair). You may obtain further information by examining the MCAI in
the AD docket.

Relevant Service Information

Airbus has issued Service Bulletin A300-53-229, Revision 5, dated
April 8,

[[Page 26963]]

1997; and Mandatory Service Bulletin A300-53-0211, Revision 07, dated
December 1, 2006. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

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

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.

Costs of Compliance

Based on the service information, we estimate that this proposed AD
would affect about 5 products of U.S. registry.
We estimate that it would take about 3,735 work-hours per product
to comply with the new basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Based on these figures, we
estimate the cost of the proposed AD on U.S. operators to be
$1,587,375, or $317,475 per product.

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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

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

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]

2. The FAA amends Sec. 39.13 by removing Amendment 39-6448 (55 FR
261, January 4, 1990) and adding the following new AD:

Airbus: Docket No. FAA-2011-0389; Directorate Identifier 2007-NM-
189-AD.

Comments Due Date

(a) We must receive comments by June 24, 2011.

Affected ADs

(b) This AD supersedes AD 90-01-10, Amendment 39-6448.

Applicability

(c) This AD applies to Airbus Model A300 B2-1C, A300 B2-203,
A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes;
certificated in any category; serial numbers 0003 through 0156
inclusive.

Subject

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

Reason

(e) The mandatory continuing airworthiness information (MCAI)
states:
This Airworthiness Directive (AD) is issued in order to prevent
cracks development in sections 13 to 18 of the fuselage between
rivets of longitudinal lap joints between frames 18 and 80 which
could affect the structural integrity of the fuselage if not
corrected.
This new AD:
--Retains the requirements of DGAC AD 1989-061-092(B)R4[which
corresponds to FAA AD 90-10-10], which is cancelled;
--Takes into account a new inspection program as detailed in
AIRBUS Service Bulletins (SB) A300-53-0211 Revision 7, which will
allow A300 aircraft to reach the Limit of Validity (LOV).
This AD has been republished to correctly refer to SB A300-53-
0211 in Note 2 of the Compliance section.

The inspection program consists of repetitive detailed inspections
for disbonding and cracking of the fuselage inner doubler; eddy
current and ultrasonic inspections of the fuselage longitudinal lap
joints for cracking; and repair if necessary (i.e., repairing any
cracking or disbonding, or contacting Airbus for repair instructions
and doing the repair).

Compliance

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

Repetitive Inspections of ``Special Areas'' and Repair or Modification
if Necessary

(g) For airplanes on which an eddy current inspection of the
``special'' areas of the longitudinal lap joints has not been done
as of the effective date of this AD in accordance with Airbus
Mandatory Service Bulletin A300-53-0211: Prior to the accumulation
of 24,000 total flight cycles, or within 2,000 flight cycles after
the effective date of this AD, whichever occurs later; do an eddy
current inspection for cracking of the ``special'' areas of the
longitudinal lap joints, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A300-53-0211,
Revision 07, dated December 1, 2006. If no cracking is found, repeat
the inspection thereafter at the applicable intervals specified in
Table 1 of this AD. If any crack is found during any inspection
required by this paragraph, repair or modify before further flight,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-53-

[[Page 26964]]

0211, Revision 07, dated December 1, 2006; and do the applicable
inspection of the repaired or modified area in accordance with
paragraph (k) of this AD. ``Special'' areas of the longitudinal lap
joints are defined in Airbus Mandatory Service Bulletin A300-53-
0211, Revision 07, dated December 1, 2006.

Table 1--Repetitive Intervals for Inspecting Special Areas of the
Longitudinal Lap Joints
------------------------------------------------------------------------
Inspect special Repeat at intervals
For airplanes-- area-- not to exceed--
------------------------------------------------------------------------
All......................... STGR5 LH and RH 3,600 flight cycles
(FR54 through FR58).
All......................... STGR22 LH and RH 2,700 flight cycles
(FR26 through FR40).
All......................... STGR22 RH (FR58 3,000 flight cycles
through FR65).
All......................... STGR31 LH/RH (FR26 3,000 flight cycles
through FR39).
MSN 003..................... STGR31 LH/RH (FR54 3,600 flight cycles
through FR58).
------------------------------------------------------------------------

(h) For airplanes on which an eddy current inspection of the
``special'' areas of the longitudinal lap joints has been done
before the effective date of this AD in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-53-0211; except for airplanes on which a repair or modification
of the ``special'' areas has been done in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-53-0211: Do the next inspection of the ``special'' areas of the
longitudinal lap joints at the earlier of the times specified in
paragraphs (h)(1) and (h)(2) of this AD, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is
found, repeat the inspection thereafter at the applicable intervals
specified in Table 2 of this AD. If any crack is found during any
inspection required by this paragraph, repair or modify before
further flight, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07,
dated December 1, 2006, and do the applicable inspection of the
repaired or modified area in accordance with paragraph (k) of this
AD. ``Special'' areas of the longitudinal lap joints are defined in
Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated
December 1, 2006.
(1) Within 6,000 flight cycles after doing the last inspection
of the ``special'' areas of the longitudinal lap joints, in
accordance with Airbus Mandatory Service Bulletin A300-53-0211.
(2) Within the applicable intervals specified in Table 2 of this
AD, or within 60 days after the effective date of this AD, whichever
occurs later.

Table 2--Repetitive Intervals for Inspecting Special Areas of the
Longitudinal Lap Joints
------------------------------------------------------------------------
Inspect special Repeat at intervals
For airplanes-- area-- not to exceed--
------------------------------------------------------------------------
All......................... STGR5 LH and RH 3,600 flight cycles
(FR54 through FR58).
All......................... STGR22 LH and RH 2,700 flight cycles
(FR26 through FR40).
All......................... STGR22 RH (FR58 3,000 flight cycles
through FR65).
All......................... STGR31 LH/RH (FR26 3,000 flight cycles
through FR39).
MSN 003..................... STGR31 LH/RH (FR54 3,600 flight cycles
through FR58).
------------------------------------------------------------------------

Repetitive Inspections of ``Standard Areas'' and Repair or Modification
If Necessary

(i) For airplanes on which an eddy current inspection of the
``standard'' areas of the longitudinal lap joints has not been done
before the effective date of this AD in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-53-0211: At the applicable time specified in Tables 3 and 4 of
this AD, do an eddy current inspection for cracking of the
longitudinal lap joints in the ``standard'' areas, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Repeat
the inspection thereafter at the applicable intervals specified in
Tables 3 and 4 of this AD. If any crack is found during any
inspection required by this paragraph, repair or modify before
further flight, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07,
dated December 1, 2006, and do the applicable inspection of the
applicable area specified in Tables 3 and 4 of this AD. ``Standard''
areas of the longitudinal lap joints are defined in Airbus Mandatory
Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

Table 3--Initial Compliance Times and Repetitive Intervals for Inspecting Standard Areas of the Longitudinal Lap
Joints
----------------------------------------------------------------------------------------------------------------
Before the accumulation Repeat at intervals
For airplanes-- of-- Inspect standard area-- not to exceed--
----------------------------------------------------------------------------------------------------------------
All............................... 32,000 total flight cycles STGR5, 13, 22 LH and RH, 3,600 flight cycles
STGR31 LH (FR18 through
FR26).
All............................... 32,000 total flight cycles STGR27 RH, STGR39 RH 8,000 flight cycles
(FR18 through FR20A,
FR25A, FR26).
All............................... 32,000 total flight cycles STGR43 LH, STGR46 RH, 5,700 flight cycles
STGR51 LH (FR19 through
FR26).
All............................... 32,000 total flight cycles STGR5 LH/RH (FR26 through 3,000 flight cycles
FR40) STGR11 LH/RH (FR27
through FR32) STGR13 LH/
RH (FR 26 through FR28,
FR31 through FR40)
STGR27 LH/RH (FR 27
through FR32) STGR43 LH/
RH (FR 26 through FR39)
STGR49 RH (FR26 through
FR39).
All............................... 32,000 total flight cycles STGR47 LH (FR26 through 5,700
FR39).

[[Page 26965]]

All............................... 32,000 total flight cycles STGR5, 13, 22 LH/RH (FR40 5,000
through FR54).
All except MSN 0003............... 32,000 total flight cycles STGR13, 44, 52 LH/RH 3,600
(FR54 through FR58)
STGR22 LH/RH (FR54,
FR55) STGR31 LH/RH (FR54
through FR58).
----------------------------------------------------------------------------------------------------------------

(j) For airplanes on which an eddy current inspection of the
``standard'' areas of the longitudinal lap joints has been done as
of the effective date of this AD in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-53-0211; except for airplanes on which a repair or modification
of the ``standard areas'' has been done in accordance with Airbus
Mandatory Service Bulletin A300-53-0211: Do the next inspection of
the ``standard'' areas of the longitudinal lap joints at the earlier
of the times specified in paragraphs (j)(1) and (j)(2) of this AD,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-53-0211, Revision 07, dated December
1, 2006. Thereafter, if no cracking is found, repeat the inspection
at the applicable intervals specified in Tables 3 and 4 of this AD.
If any crack is found during any inspection required by this
paragraph, repair or modify before further flight, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do
the applicable inspection of the repaired or modified area in
accordance with paragraph (k) of this AD. ``Standard'' areas of the
longitudinal lap joints are defined in Airbus Mandatory Service
Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

Table 4--Initial Compliance Times and Repetitive Intervals for Inspecting Additional Standard Areas of the
Longitudinal Lap Joints
----------------------------------------------------------------------------------------------------------------
Before the accumulation Repeat at intervals
For airplanes-- of-- Inspect standard area-- not to exceed--
----------------------------------------------------------------------------------------------------------------
Pre-Mod 1398...................... 32,000 total flight cycles STGR5, 13 LH/RH 22 LH 2,700 flight cycles
(FR58 through FR65)
STGR31 LH (FR58 through
FR72) STGR31 RH (FR65
through FR72).
All............................... 32,000 total flight cycles STGR27 RH, STGR39 RH 8,000 flight cycles
(FR58, FR59A, FR63A
through FR65).
Post-Mod 1398..................... 32,000 total flight cycles STGR5, 13 LH/RH 22 LH 3,000 flight cycles
(FR58 through FR65)
STGR31 LH (FR58 through
FR72) STGR 31 RH (FR65
through FR72).
Pre-Mod 1398...................... 32,000 total flight cycles STGR5, 13, 22 LH/RH (FR65 2,300 flight cycles
through FR72).
Post-Mod 1398..................... 32,000 total flight cycles STGR5, 13, 22 LH/RH (FR65 3,000 flight cycles
through FR72).
All............................... 32,000 total flight cycles STGR44 LH (FR58 through 3,000 flight cycles
FR72) STGR52 LH/RH (FR58
through FR65) STGR47 RH
(FR58 through FR72)
STGR57 LH (FR65 through
FR72).
All............................... 24,000 total flight cycles STGR22 RH (FR58 through 3,000 flight cycles
FR65).
All............................... 32,000 total flight cycles STGR6 LH/RH (FR72 through 3,000 flight cycles
FR80) STGR24 LH/RH (FR76
through FR80).
All............................... 32,000 total flight cycles STRG17 LH/RH (FR76 5,700 flight cycles
through FR80) STGR29 LH/
RH (FR72 through FR76).
STGR35 LH/RH (FR72
through FR80).
All............................... 27,000 total flight cycles STGR51 LH/RH (FR72 5,700 flight cycles
through FR80).
----------------------------------------------------------------------------------------------------------------

(1) Within the applicable time in paragraph (j)(1)(i) or
(j)(1)(ii) of this AD after doing the last inspection of the
``standard'' areas of the longitudinal lap joints in accordance with
Airbus Mandatory Service Bulletin A300-53-0211.
(i) For longitudinal lap joints with bonded doublers: 6,000
flight cycles.
(ii) For longitudinal lap joints without bonded doublers: 8,000
flight cycles.
(2) Within the applicable time specified in Tables 3 or 4 of
this AD, or within 60 days after the effective date of this AD,
whichever occurs later.

Post-Repair or Modification Inspections and Repair or Modification if
Necessary

(k) For airplanes on which a repair or modification has been
done in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-53-0211: At the applicable initial
inspection time specified in Table 5 of this AD, do an eddy current
inspection for cracking of the repaired or modified areas, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
If no cracking is found, repeat the inspection thereafter at the
applicable intervals specified

[[Page 26966]]

in Table 5 of this AD. If any crack is found during any inspection
required by this paragraph, repair or modify before further flight,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-53-0211, Revision 07, dated December
1, 2006.

Table 5--Post-Repair or Modification Compliance Time
----------------------------------------------------------------------------------------------------------------
Repair or retrofit solution/area--as
identified in airbus mandatory Initial inspection after Follow-up inspections at intervals not to
service bulletin A300-53-0211 repair or retrofit-- exceed--
----------------------------------------------------------------------------------------------------------------
Repair 1: (Without cut out) also Skin/doubler thickness....... 1,000 flight cycles.
applicable to the solution with < 1 inch: 10,000
removed inner doubler. flight cycles after repair.
= 1 inch 2,000 flight cycles.
and < 2 inch: 30,000 flight
cycles after repair.
= 2 inch: 6,400 flight cycles.
60,000 flight cycles after
repair.
Repair 4 (With cut out).............. Within 32,000 flight cycles 5,000 flight cycles.
after repair.
Repair 4A (With cut out)............. Within 24,000 flight cycles 5,300 flight cycles.
after repair.
Repair 7 (MSN 0095 at STGR52 LH in Within 37,000 flight cycles 12,000 flight cycles.
Section 16). after repair.
Repair 9 (MSN 0073 and 0095 STGR44 LH/ Within 36,000 flight cycles 5,000 flight cycles.
RH in Sections 16 and 17). after repair.
Repair 10 (Post-repair inspections in Within 20,000 flight cycles 11,000 flight cycles.
Figure 13). after repair.
Repair 2 (With cut out).............. Within 24,000 flight cycles 5,300 flight cycles.
after repair.
Repair 3 (Without cut out)........... Within 24,000 flight cycles 5,300 flight cycles.
after repair.
Retrofit 1 (Retrofit lap joint)...... Within 32,000 flight cycles 5,000 flight cycles.
after retrofit.
Retrofit 2 Retrofit lower shell (4 Within 32,000 flight cycles 3,000 flight cycles.
panel solution) STGR43 LH (FR26 after retrofit.
through FR39), STGR43 RH (FR26
through FR38), and STGR49 RH (FR26
through FR38).
Retrofit 2 Retrofit lower shell (4 Within 32,000 flight cycles 5,700 flight cycles.
panel solution) STGR 46 RH (FR19 after retrofit.
through FR26), and STGR47 LH (FR26
through FR39), and STGR51 LH (FR19
through FR26).
Retrofit 3 Retrofit lower shell (3 Within 32,000 flight cycles 3,000 flight cycles.
panel solution) STGR43 LH (FR26 after retrofit.
through FR39), and STGR43 RH (FR26
through FR38).
Retrofit 3 Retrofit lower shell (3 Within 32,000 flight cycles 5,700 flight cycles.
panel solution) STGR46 RH (FR19 after retrofit.
through FR26), and STGR51 LH (FR19
through FR26), and STGR 54 LH (FR26
through FR39).
Retrofit 3A (STGR43 LH/RH between Within 32,000 flight cycles 5,000 flight cycles.
FR37 and FR39 in Section 14). after retrofit.
Retrofit 4 (Retrofit lap joint Within 42,000 flight cycles 5,000 flight cycles.
without cut out). after retrofit.
Retrofit 5 (Retrofit lap joint)...... Within 42,000 flight cycles 5,000 flight cycles.
after retrofit.
Retrofit 6 (Retrofit lap joint)...... Within 34,000 flight cycles 12,000 flight cycles.
after retrofit.
Retrofit 7 (Retrofit lap joint)...... Within 47,600 flight cycles 5,400 flight cycles.
after retrofit.
----------------------------------------------------------------------------------------------------------------

Fuselage Inner Doubler Inspections and Repair if Necessary

(l) For airplanes on which any inspections of the fuselage
bonded inner doublers of the longitudinal lap joints in Sections 13
through 18 (except Sections 16 and 17 at Stringer 31 left-hand and
right-hand) for disbonding and cracking have not been done as of the
effective date of this AD in accordance with Airbus Service Bulletin
A300-53-229: Prior to the accumulation of 24,000 total flight cycles
or within 15 years since new, whichever occurs first; or within 60
days after the effective date of this AD; whichever occurs later, do
a detailed inspection of the fuselage bonded inner doublers of the
longitudinal lap joints in Sections 13 through 18 (except Sections
16 and 17 at Stringer 31 left-hand and right-hand) for disbonding
and cracking, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8,
1997. If no disbonding and no cracking is found, repeat the
inspection thereafter at the applicable intervals specified in Table
6 of this AD.

Table 6--Repetitive Intervals for Inspections for Disbonding and
Cracking
------------------------------------------------------------------------
Inspect at intervals not to exceed--
For area--
------------------------------------------------------------------------
Sections 13 and 14 as specified in Within 7 years or 12,000 flight
Airbus Service Bulletin A300-53- cycles after doing the inspection,
229. whichever occurs first.
Sections 15 through 18 as Within 8.5 years or 12,000 flight
specified in Airbus Service cycles after doing the inspection,
Bulletin A300-53-229. whichever occurs first.
------------------------------------------------------------------------

(1) If no cracking is found and ``minor'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, is found: Repeat the
inspection thereafter at intervals not to exceed 1 year for areas
below stringer 22, and at intervals not to exceed 2 years for areas
above and including stringer 22.
(2) If no cracking is found and ``major'' disbonding, as defined
in Airbus Service Bulletin A300-53-229, is found: Within 1,000
flight cycles after doing the inspection, repair, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
(m) For airplanes on which any inspections of the fuselage
bonded inner doublers of the longitudinal lap joints in Sections 13
through 18 (except Sections 16 and 17 at Stringer 31 left-hand and
right-hand) for disbonding and cracking have been done as of the
effective date of this AD in accordance with Airbus Service Bulletin
A300-53-229; except for airplanes on which a repair of that area has
been done in accordance with Airbus Service

[[Page 26967]]

Bulletin A300-53-229: At the applicable time specified in Table 6 of
this AD, or within 60 days after the effective date of this AD,
whichever occurs later, do a detailed inspection of the fuselage
bonded inner doublers of the longitudinal lap joints in Sections 13
through 18 (except Sections 16 and 17 at Stringer 31 left-hand and
right-hand) for disbonding and cracking, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-229,
Revision 5, dated April 8, 1997. If no disbonding and no cracking is
found, repeat the inspection at the applicable intervals specified
in Table 6 of this AD.
(1) If no cracking is found and ``minor'' disbonding, as defined
in Airbus Service Bulletin A300-53-229, is found: Repeat the
inspection thereafter at intervals not to exceed 1 year for areas
below stringer 22, and at intervals not to exceed 2 years for areas
above and including stringer 22.
(2) If no cracking is found and ``major'' disbonding, as defined
in Airbus Service Bulletin A300-53-229, is found: Within 1,000
flight cycles after doing the inspection, repair, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
(n) For airplanes on which any inspections of the fuselage
bonded inner doublers of the longitudinal lap joints in Sections 16
and 17 at Stringer 31 left-hand and right-hand for disbonding and
cracking have not been done as of the effective date of this AD in
accordance with Airbus Service Bulletin A300-53-229: Prior to the
accumulation of 24,000 total flight cycles or within 12 years since
new, whichever occurs first; or within 60 days after the effective
date of this AD; whichever occurs later, do a detailed inspection of
the fuselage bonded inner doubles of the longitudinal lap joints in
Sections 16 and 17 at Stringer 31 left-hand and right-hand for
disbonding and cracking, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997. If no disbonding and no cracking is found,
repeat the inspection thereafter at intervals not to exceed 7 years
or 12,000 flight cycles, whichever occurs first.
(1) If no cracking is found and ``minor'' disbonding, as defined
in Airbus Service Bulletin A300-53-229, is found: Repeat the
inspection thereafter at intervals not to exceed 1 year for areas
below stringer 22, and at intervals not to exceed 2 years for areas
above and including stringer 22. Doing a repair in accordance with
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8,
1997, terminates the repetitive inspections required by this
paragraph for that area.
(2) If no cracking is found and ``major'' disbonding, as defined
in Airbus Service Bulletin A300-53-229, is found: Within 1,000
flight cycles after doing the inspection, repair, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
(o) For airplanes on which any inspections of the fuselage
bonded inner doublers of the longitudinal lap joints in Sections 16
and 17 at Stringer 31 left-hand and right-hand for disbonding and
cracking have been done as of the effective date of this AD in
accordance with Airbus Service Bulletin A300-53-229; except
airplanes on which a repair of that area has been done in accordance
with Airbus Service Bulletin A300-53-229: Within 7 years or 12,000
flight cycles after doing the inspection, whichever occurs first; or
within 60 days after the effective date of this AD; whichever occurs
later, do a detailed inspection of the fuselage bonded inner doubles
of the longitudinal lap joints in Sections 16 and 17 at Stringer 31
left-hand and right-hand for disbonding and cracking in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and
corrosion are found, repeat the inspection thereafter at intervals
not to exceed 7 years or 12,000 flight cycles, whichever occurs
first.
(1) If no cracking is found and ``minor'' disbonding, as defined
in Airbus Service Bulletin A300-53-229, is found: Repeat the
inspection thereafter at intervals not to exceed 1 year for areas
below stringer 22, and at intervals not to exceed 2 years for areas
above and including stringer 22. Doing a repair in accordance with
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8,
1997, terminates the repetitive inspections required by this
paragraph for that area.
(2) If no cracking is found and ``major'' disbonding, as defined
in Airbus Service Bulletin A300-53-229, is found: Within 1,000
flight cycles after doing the inspection, repair, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
(p) Although Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997; and Airbus Mandatory Service Bulletin A300-53-
0211, Revision 07, dated December 1, 2006; specify to submit certain
information to the manufacturer, this AD does not include that
requirement.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service
information as follows:
(1) Although the MCAI or service information allows further
flight after cracks are found during compliance with the required
action, this AD requires that you repair the crack(s) before further
flight.
(2) The MCAI or service information does not include enforceable
compliance times for certain actions; however, this AD requires that
those actions be done at the enforceable times specified in this AD.
(3) Although the MCAI or service information tells you to submit
information to the manufacturer, paragraph (p) of this AD specifies
that such submittal is not required.

Other FAA AD Provisions

(q) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-2125; fax (425) 227-1149. Information may be e-mailed 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 or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.

Related Information

(r) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2007-0091, dated April 10, 2007, corrected June 23, 2008;
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8,
1997; and Airbus Mandatory Service Bulletin A300-53-0211, Revision
07, dated December 1, 2006; for related information.

Issued in Renton, Washington, on April 28, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-11335 Filed 5-9-11; 8:45 am]
BILLING CODE 4910-13-P

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