Airworthiness Directives; Airbus Model A310 Series Airplanes, 50-56 [2010-32992]

Download as PDF 50 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 2074, Revision 03, dated October 13, 2006, are considered acceptable for compliance with the corresponding action specified in this AD. DEPARTMENT OF TRANSPORTATION FAA AD Differences 14 CFR Part 39 Note 2: This AD differs from the MCAI and/or service information as follows: The MCAI and service information do not specify a corrective action if cracking is found and the radius of the rework is 20.0 mm (0.787 inch) or more. Paragraph (g)(3)(i)(B) of this AD requires repair in accordance with a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent). [Docket No. FAA–2010–1274; Directorate Identifier 2010–NM–090–AD] Federal Aviation Administration Other FAA AD Provisions (k) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information 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. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. srobinson on DSKHWCL6B1PROD with PROPOSALS Related Information (l) Refer to MCAI EASA Airworthiness Directive 2009–0058, dated March 13, 2009; and Airbus Mandatory Service Bulletin A310–53–2074, Revision 04, dated October 24, 2008; for related information. Issued in Renton, Washington, on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–32991 Filed 12–30–10; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 19:10 Dec 30, 2010 Jkt 223001 RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Airbus Model A310 Series 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. 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: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) * * * was issued to require a set of inspection and modification tasks which addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25–571 requirements related to damage-tolerance and fatigue evaluation of structure. * * * * * * * * The unsafe condition is reduced structural integrity of the wings. 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 February 17, 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; PO 00000 Frm 00023 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. Fmt 4702 Sfmt 4702 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–2010–1274; Directorate Identifier 2010–NM–090–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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0057, dated March 13, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) original E:\FR\FM\03JAP1.SGM 03JAP1 51 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules issue up to revision 7 was issued to require a set of inspection and modification tasks which addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25– 571 requirements related to damage-tolerance and fatigue evaluation of structure. Following the Extended Design Service Goal activities as part of the Structure Task Group for the Airbus A310 program, EASA published AD 2007–0053, which replaced DGAC France AD F–1992–106–132R7. Since the issuance of AD 2007–0053R1, the thresholds and the intervals of Airbus Service Bulletins (SB) A310–57–2050 and A310–57–2064 have been updated. Consequently, this new [EASA] AD takes over the requirements of paragraphs 1.15 and 1.17 of EASA AD 2007–0053R1, which has been revised accordingly * * * and requires the accomplishment of Airbus SB A310–57– 2048 at revision 01. • Directorate Identifier 2010–NM– 092–AD. That NPRM proposes to supersede AD 98–26–01, amendment 39–10942 (63 FR 69179, December 16, 1998), to continue to require certain actions specified in that AD. However, that NPRM does not restate paragraphs (p) and (r) of AD 98–26–01. Instead, certain requirements of paragraphs (p) and (r) of that AD are included in this NPRM, Directorate Identifier 2010–NM– 090–AD. • Directorate Identifiers 2010–NM– 089–AD and 2010–NM–091–AD. Both of these NPRMs include the requirements of certain other paragraphs of AD 98– 26–01. The unsafe condition is reduced structural integrity of the wings. The required actions are as follows, depending on airplane configuration: • Cold working of trellis boom drainage holes. • Repetitive detailed or rotating probe inspections for cracking in the drain holes on the lower skin panel in the center wing box between frames 42 and 46 and corrective actions if necessary. Corrective actions include repairing cracking and contacting the FAA or EASA for repair and doing the repair. • Repetitive eddy current inspections for cracking of the upper corner angle fitting and the vertical tee fitting at left and right frame 40, and corrective actions if necessary. Corrective actions include repairing, replacing the internal angle fitting and contacting the FAA or EASA for repair and doing the repair. You may obtain further information by examining the MCAI in the AD docket. Other Relevant Rulemaking We are considering issuing three other NPRMs related to this NPRM: Airbus has issued the service bulletins listed in the table that follows: Relevant Service Information TABLE—SERVICE INFORMATION Service bulletin Revision Airbus Mandatory Service Bulletin A310–57–2048 ....................................................... Airbus Mandatory Service Bulletin A310–57–2050, including Appendix 01 ................. Airbus Mandatory Service Bulletin A310–57–2064, including Appendix 1 ................... 01 ................................................. 02 ................................................. 02 ................................................. 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. srobinson on DSKHWCL6B1PROD with PROPOSALS 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. VerDate Mar<15>2010 19:10 Dec 30, 2010 Jkt 223001 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 44 products of U.S. registry. We also estimate that it would take about 137 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $512,380, or $11,645 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 PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 Date May 22, 2007. August 27, 2009. December 21, 2007. 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 E:\FR\FM\03JAP1.SGM 03JAP1 52 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules Comments Due Date (a) We must receive comments by February 17, 2011. this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 571 requirements related to damage-tolerance and fatigue evaluation of structure. * * *. * Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Affected ADs The Proposed Amendment (c) This AD applies to Airbus Model A310– 203, –204, –221, –222, –304, –322, –324, and –325 airplanes, certificated in any category, all serial numbers. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (b) None. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. 1. The authority citation for part 39 continues to read as follows: Reason § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2010–1274; Directorate Identifier 2010–NM–090–AD. * * * Compliance Applicability PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. * The unsafe condition is reduced structural integrity of the wings. (e) The mandatory continuing airworthiness information (MCAI) states: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) original issue up to revision 7 was issued to require a set of inspection and modification tasks which addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25– (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. Cold Working of Trellis Boom Drainage Holes (g) For Model A310–203, –204, –222, –304, –322 and –324 airplanes, except airplanes identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Within the applicable time specified in Table 1 of this AD, cold work the trellis boom drainage holes, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–57– 2048, Revision 01, dated May 22, 2007. Certain compliance times specified in Table 1 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 3.6 hours; or long range use, AFT exceeding 3.6 hours. TABLE 1—COMPLIANCE TIMES FOR PARAGRAPH (G) OF THIS AD Airplanes, as identified in Airbus mandatory service bulletin A310–57–2048, revision 01, dated May 22, 2007 Configuration 01 airplanes ................................. Configuration 02 airplanes ................................. Configuration 03 short range airplanes .............. Configuration 03 long range airplanes ............... (1) Airplanes on which Airbus modification 06130 was done in production. (2) Airplanes on which Airbus Mandatory Service Bulletin A310–57–2048 was done in service. (3) Airplanes on which rework of cracked drain holes was done in accordance with Airbus Mandatory Service Bulletin A310–57– 2050. Compliance time (whichever occurs later) Prior to the accumulation of 31,800 total flight cycles or 63,600 total flight hours, whichever occurs first. Prior to the accumulation of 40,000 total flight cycles or 80,000 total flight hours, whichever occurs first. Prior to the accumulation of 30,950 total flight cycles or 86,750 total flight hours, whichever occurs first. Prior to the accumulation of 24,100 total flight cycles or 120,600 total flight hours, whichever occurs first. Inspection of Trellis Boom Drainage Holes (h) For all airplanes: Within the applicable intervals specified in Table 2 of this AD, perform a detailed or rotating probe inspection for cracking in the drain holes on the lower skin panel in the center wing box between frames 42 and 46, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–57– Within 6 months after the effective date of this AD. Within 6 months after the effective date of this AD. Within 6 months after the effective date of this AD. Within 6 months after the effective date of this AD. 2050, Revision 02, dated August 27, 2009. Repeat the inspections thereafter at intervals not to exceed the applicable times specified in Table 3 of this AD. Certain compliance times specified in Tables 2 and 3 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 3.6 hours; or long range use, AFT exceeding 3.6 hours. TABLE 2—COMPLIANCE TIMES FOR PARAGRAPH (H) OF THIS AD srobinson on DSKHWCL6B1PROD with PROPOSALS Airplanes, as identified in Airbus mandatory service bulletin A310–57–2050, revision 02, dated August 27, 2009 Configuration 01 airplanes ................................. VerDate Mar<15>2010 19:10 Dec 30, 2010 Jkt 223001 Compliance time (whichever occurs later) Prior to the accumulation of 17,800 total flight cycles or 35,600 total flight hours, whichever occurs first. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD. E:\FR\FM\03JAP1.SGM 03JAP1 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 53 TABLE 2—COMPLIANCE TIMES FOR PARAGRAPH (H) OF THIS AD—Continued Airplanes, as identified in Airbus mandatory service bulletin A310–57–2050, revision 02, dated August 27, 2009 Configuration 02 airplanes on which Airbus Mandatory Service Bulletin A310–57–2048 has been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57– 2048, Revision 01, dated May 22, 2007. Configuration 02 airplanes on which Airbus Mandatory Service Bulletin A310–57–2048 has not been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 22, 2007. Configuration 03 airplanes ................................. Configuration 04 airplanes ................................. Configuration 05 airplanes on which Airbus Mandatory Service Bulletin A310–57–2048 has been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57– 2048, Revision 01, dated May 22, 2007. Configuration 05 airplanes on which Airbus Mandatory Service Bulletin A310–57–2048 has not been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 22, 2007. Configuration 06 short range airplanes .............. Configuration 06 long range airplanes ............... Configuration 07 short range airplanes .............. srobinson on DSKHWCL6B1PROD with PROPOSALS Configuration 07 long range airplanes ............... Configuration 08 short range airplanes on which Airbus Mandatory Service Bulletin A310–57–2048 has been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 22, 2007. VerDate Mar<15>2010 19:10 Dec 30, 2010 Jkt 223001 Compliance time (whichever occurs later) Within 32,850 flight cycles or 65,700 flight hours, whichever occurs first, after accomplishing Airbus Mandatory Service Bulletin A310–57–2048. Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD. Within 8,600 flight cycles or 17,250 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310– 57–2048; OR Within 11,400 flight cycles or 22,800 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin A310–57–2048. Prior to the accumulation of 22,300 total flight cycles or 44,550 total flight hours, whichever occurs first. Prior to the accumulation of 41,550 total flight cycles or 83,100 total flight hours, whichever occurs first. Prior to the accumulation of 40,000 total flight cycles or 80,000 total flight hours, whichever occurs first. Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD. Within 10,600 flight cycles or 21,150 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310– 57–2048; OR Within 13,900 flight cycles or 27,800 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin A310–57–2048. Prior to the accumulation of 17,250 total flight cycles or 48,400 total flight hours, whichever occurs first. Prior to the accumulation of 13,450 total flight cycles or 67,250 total flight hours, whichever occurs first. Prior to the accumulation of 32,150 total flight cycles or 90,050 total flight hours, whichever occurs first. Prior to the accumulation of 25,050 total flight cycles or 125,150 total flight hours, whichever occurs first. Prior to the accumulation of 30,950 total flight cycles or 86,750 total flight hours, whichever occurs first. Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD. PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD. Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD. Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD. Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD. Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD. Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD. Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD. Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD. E:\FR\FM\03JAP1.SGM 03JAP1 54 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules TABLE 2—COMPLIANCE TIMES FOR PARAGRAPH (H) OF THIS AD—Continued Airplanes, as identified in Airbus mandatory service bulletin A310–57–2050, revision 02, dated August 27, 2009 Compliance time (whichever occurs later) Configuration 08 short range airplanes on which Airbus Mandatory Service Bulletin A310–57–2048 has not been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 22, 2007. Configuration 08 long range airplanes on which Airbus Mandatory Service Bulletin A310–57– 2048 has been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 22, 2007. Configuration 08 long range airplanes on which Airbus Mandatory Service Bulletin A310–57– 2048 has not been done within the ‘‘recommended’’ compliance times specified in paragraph 1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 22, 2007. Within 8,200 flight cycles or 23,000 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310– 57–2048; OR Within 10,800 flight cycles or 30,300 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin A310–57–2048. Prior to the accumulation of 24,100 total flight cycles or 120,600 total flight hours, whichever occurs first. Within 6,400 flight cycles or 31,950 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310– 57–2048; OR Within 8,400 flight cycles or 42,150 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin A310–57–2048. Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD. Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD. Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD. TABLE 3—REPETITIVE INTERVALS FOR PARAGRAPH (H) OF THIS AD, DEPENDING ON MOST RECENT INSPECTION TYPE Airplanes, as identified in Airbus mandatory service bulletin A310–57–2050, revision 02, dated August 27, 2009 Type of inspection done during most recent inspection Repetitive interval (not to exceed) Configuration 01 and 02 airplanes ............. Detailed inspection ....................... Rotating probe inspection ............ Configurations 03, 04, and 05 airplanes .... Detailed inspection ....................... 8,600 flight cycles or 17,250 flight hours, whichever occurs first. 11,400 flight cycles or 22,800 flight hours, whichever occurs first. 10,600 flight cycles or 21,150 flight hours, whichever occurs first. 13,900 flight cycles or 27,800 flight hours, whichever occurs first. 8,200 flight cycles or 23,000 flight hours, whichever occurs first. Rotating probe inspection ............ Configurations 06, 07, and 08 short range airplanes. Detailed inspection ....................... Rotating probe inspection ............ srobinson on DSKHWCL6B1PROD with PROPOSALS Detailed inspection ....................... Rotating probe inspection ............ Configurations 06, 07, and 08 long range airplanes. 10,800 flight cycles or 30,300 flight hours, whichever occurs first. 6,400 flight cycles or 31,950 flight hours, whichever occurs first. 8,400 flight cycles or 42,150 flight hours, whichever occurs first. Corrective Actions for Paragraph (h) of This AD (i) If any cracking is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–57–2050, Revision 02, dated August 27, 2009; except where the service bulletin specifies to contact Airbus, before further flight, repair in VerDate Mar<15>2010 19:10 Dec 30, 2010 Jkt 223001 accordance with a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent). Inspection of Fuselage Frame 40 Upper Corner Fitting (j) For all airplanes: Within the applicable time specified in Table 4 of this AD, perform an eddy current inspection for cracking of the upper corner fitting at left and right frame 40, PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–57–2064, Revision 02, dated December 21, 2007. Repeat the inspections thereafter at intervals not to exceed the applicable times specified in Table 5 of this AD. Certain compliance times specified in Tables 4 and 5 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 3.23 hours; or long range use, AFT exceeding 3.23 hours. E:\FR\FM\03JAP1.SGM 03JAP1 55 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules TABLE 4—COMPLIANCE TIMES FOR PARAGRAPH (J) OF THIS AD Airplane configurations identified in Airbus mandatory service bulletin A310–57–2064, revision 02, dated December 21, 2007 Compliance time (whichever occurs later) Model A310–203, –204, –221, and –222 airplanes identified as Configuration 01. Prior to the accumulation cycles or 30,300 total ever occurs first. Model A310–203, –204, –221, and –222 air- Prior to the accumulation planes identified as Configurations 02 and 03. cycles or 42,800 total ever occurs first. Model A310–304, –322, –324, and –325 short Prior to the accumulation range airplanes identified as Configuration 01. cycles or 41,300 total ever occurs first. Model A310–304, –322, –324, and –325 short Prior to the accumulation range airplanes identified as Configurations cycles or 58,300 total 02 and 03. ever occurs first. Model A310–304, –322, –324, and –325 long Prior to the accumulation range airplanes identified as Configuration 01. cycles or 64,000 total ever occurs first. Model A310–304, –322, –324, and –325 long Prior to the accumulation range airplanes identified as Configurations cycles or 90,400 total 02 and 03. ever occurs first. of 15,100 total flight flight hours, whichof 21,400 total flight flight hours, whichof 14,700 total flight flight hours, whichof 20,700 total flight flight hours, whichof 12,800 total flight flight hours, whichof 18,000 total flight flight hours, which- Within 1,300 flight cycles or 2,700 flight hours, whichever occurs first, after the effective date of this AD. Within 1,300 flight cycles or 2,700 flight hours, whichever occurs first, after the effective date of this AD. Within 600 flight cycles or 1,800 flight hours, whichever occurs first, after the effective date of this AD. Within 600 flight cycles or 1,800 flight hours, whichever occurs first, after the effective date of this AD. Within 500 flight cycles or 2,650 flight hours, whichever occurs first, after the effective date of this AD. Within 500 flight cycles or 2,650 flight hours, whichever occurs first, after the effective date of this AD. TABLE 5—REPETITIVE INTERVALS FOR PARAGRAPH (J) OF THIS AD Repetitive interval (not to exceed) Airplanes Model A310–203, –204, –221, and –222 airplanes ................................. Model A310–304, –322, –324, and –325 short range airplanes .............. Model A310–304, –322, –324, and –325 long range airplanes ............... 8,750 flight cycles or 17,550 flight hours, whichever occurs first. 5,800 flight cycles or 16,300 flight hours, whichever occurs first. 4,800 flight cycles or 24,050 flight hours, whichever occurs first. srobinson on DSKHWCL6B1PROD with PROPOSALS Corrective Actions for Paragraph (h) of This AD (k) If, during any inspection required by paragraph (j) of this AD, any crack is found, prior to further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–57–2064, Revision 02, dated December 21, 2007; except where the service bulletin specifies to contact Airbus, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent). acceptable for compliance with the corresponding actions specified in paragraphs (h) and (i) of this AD. (n) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310–57–2064, dated August 24, 1995; or Revision 01, dated January 5, 2001; are acceptable for compliance with the corresponding actions specified in paragraphs (j) and (k) of this AD. Credit for Actions Accomplished in Accordance With Previous Service Information (l) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A310–57–2048, dated April 23, 1990, are considered acceptable for compliance with the corresponding action specified in paragraph (g) of this AD. (m) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A310–57–2050, dated April 23, 1990; or Airbus Mandatory Service Bulletin A310–57–2050, Revision 01, dated May 22, 2007; are considered Other FAA AD Provisions (o) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information 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. Before using any approved AMOC on any airplane to FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No Differences. which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (p) Refer to MCAI EASA Airworthiness Directive 2009–0057, dated March 13, 2009, and the service bulletins listed in Table 6 of this AD, for related information. TABLE 6—SERVICE INFORMATION Service bulletin Revision Airbus Mandatory Service Bulletin A310–57–2048 ....................................................... Airbus Mandatory Service Bulletin A31–57–2050 ........................................................ 01 ................................................. 02 ................................................. VerDate Mar<15>2010 19:10 Dec 30, 2010 Jkt 223001 PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 E:\FR\FM\03JAP1.SGM 03JAP1 Date May 22, 2007. August 27, 2009. 56 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules TABLE 6—SERVICE INFORMATION—Continued Service bulletin Revision Airbus Mandatory Service Bulletin A310–57–2064 ....................................................... 02 ................................................. Issued in Renton, Washington on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. DEPARTMENT OF DEFENSE Office of the Secretary [Docket ID: DOD–2010–OS–0183] 32 CFR Part 311 Privacy Act; Implementation Office of the Secretary, DoD. Proposed rule. AGENCY: srobinson on DSKHWCL6B1PROD with PROPOSALS SUMMARY: The Office of the Secretary of Defense is exempting those records contained in DMDC 15 DoD, entitled ‘‘Armed Services Military Accession Testing’’ when the record includes the specific answers submitted and the answer key. Releasing this information to the individual will compromise the objectivity or fairness of the test if the correct or incorrect answers are released. DATES: Comments must be received on or before March 4, 2011 to be considered by this agency. ADDRESSES: You may submit comments, identified by docket number and/or RIN number and title, by any of the following methods: • Federal Rulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. • Mail: Federal Docket Management System Office, Room 3C843, 1160 Defense Pentagon, Washington, DC 20301–1160. Instructions: All submissions received must include the agency name and docket number or Regulatory Information Number (RIN) for this Federal Register document. The general policy for comments and other submissions from members of the public is to make these submissions available for public viewing on the Internet at https://www.regulations.gov as they are received without change, including any personal identifiers or contact information. FOR FURTHER INFORMATION CONTACT: Mrs. VerDate Mar<15>2010 19:10 Dec 30, 2010 Jkt 223001 Executive Order 13132, ‘‘Federalism’’ Executive Order 12866, ‘‘Regulatory Planning and Review’’ BILLING CODE 4910–13–P Cindy Allard at (703) 588–6830. December 21, 2007. SUPPLEMENTARY INFORMATION: [FR Doc. 2010–32992 Filed 12–30–10; 8:45 am] ACTION: Date It has been determined that the Privacy Act rules for the Department of Defense do not have federalism implications. The rule does not have substantial direct effects 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. It has been determined that Privacy Act rules for the Department of Defense are not significant rules. The rules do not (1) Have an annual effect on the economy of $100 million or more or adversely affect in a material way the economy; a sector of the economy; productivity; competition; jobs; the environment; public health or safety; or State, local, or Tribal governments or communities; (2) Create a serious inconsistency or otherwise interfere with an action taken or planned by another Agency; (3) Materially alter the budgetary impact of entitlements, grants, user fees, or loan programs, or the rights and obligations of recipients thereof; or (4) Raise novel legal or policy issues arising out of legal mandates, the President’s priorities, or the principles set forth in this Executive order. Public Law 96–354, ‘‘Regulatory Flexibility Act’’ (5 U.S.C. Chapter 6) It has been determined that this Privacy Act rule for the Department of Defense does not have significant economic impact on a substantial number of small entities because it is concerned only with the administration of Privacy Act systems of records within the Department of Defense. Public Law 95–511, ‘‘Paperwork Reduction Act’’ (44 U.S.C. Chapter 35) It has been determined that this Privacy Act rule for the Department of Defense imposes no information requirements beyond the Department of Defense and that the information collected within the Department of Defense is necessary and consistent with 5 U.S.C. 552a, known as the Privacy Act of 1974. Section 202, Public Law 104–4, ‘‘Unfunded Mandates Reform Act’’ It has been determined that this Privacy Act rulemaking for the Department of Defense does not involve a Federal mandate that may result in the expenditure by State, local and Tribal governments, in the aggregate, or by the private sector, of $100 million or more and that such rulemaking will not significantly or uniquely affect small governments. PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 List of Subjects in 32 CFR Part 311 Privacy. Accordingly, 32 CFR part 311 is proposed to be amended to read as follows: PART 311—OFFICE OF THE SECRETARY OF DEFENSE AND JOINT STAFF PRIVACY PROGRAM 1. The authority citation for 32 CFR part 311 continues to read as follows: Authority: Pub. L. 93–579, 88 Stat. 1986 (5 U.S.C. 522a). 2. Section 311.8 is amended by adding paragraph (c)(16) to read as follows: § 311.8 Procedures for exemptions. * * * * * (c) * * * (16) System identifier and name: DMDC 15 DoD, Armed Services Military Accession Testing. (i) Exemption: Testing or examination material used solely to determine individual qualifications for appointment or promotion in the Federal service or military service may be exempt pursuant to 5 U.S.C. 552a (k)(6), if the disclosure would compromise the objectivity or fairness of the test or examination process. Therefore, portions of the system of records may be exempt pursuant to 5 U.S.C. 552a(d). (ii) Authority: 5 U.S.C. 552a(k)(6). (iii) Reasons: (A) An exemption is required for those portions of the Skill Qualification Test system pertaining to individual item responses and scoring keys to preclude compromise of the test and to ensure fairness and objectivity of the evaluation system. (B) From subsection (d)(1) when access to those portions of the Skill Qualification Test records would reveal the individual item responses and E:\FR\FM\03JAP1.SGM 03JAP1

Agencies

[Federal Register Volume 76, Number 1 (Monday, January 3, 2011)]
[Proposed Rules]
[Pages 50-56]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32992]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1274; Directorate Identifier 2010-NM-090-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A310 Series 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. 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:

DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France AD 1992-106-132(B) * * * was issued to require a set of
inspection and modification tasks which addressed JAR/FAR [Joint
Aviation Regulation/Federal Aviation Regulation] 25-571 requirements
related to damage-tolerance and fatigue evaluation of structure. * *
*
* * * * *

The unsafe condition is reduced structural integrity of the wings. 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 February 17,
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-2010-1274;
Directorate Identifier 2010-NM-090-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

The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2009-0057, dated March 13, 2009 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France AD 1992-106-132(B) original

[[Page 51]]

issue up to revision 7 was issued to require a set of inspection and
modification tasks which addressed JAR/FAR [Joint Aviation
Regulation/Federal Aviation Regulation] 25-571 requirements related
to damage-tolerance and fatigue evaluation of structure.
Following the Extended Design Service Goal activities as part of
the Structure Task Group for the Airbus A310 program, EASA published
AD 2007-0053, which replaced DGAC France AD F-1992-106-132R7.
Since the issuance of AD 2007-0053R1, the thresholds and the
intervals of Airbus Service Bulletins (SB) A310-57-2050 and A310-57-
2064 have been updated.
Consequently, this new [EASA] AD takes over the requirements of
paragraphs 1.15 and 1.17 of EASA AD 2007-0053R1, which has been
revised accordingly * * * and requires the accomplishment of Airbus
SB A310-57-2048 at revision 01.

The unsafe condition is reduced structural integrity of the wings. The
required actions are as follows, depending on airplane configuration:
Cold working of trellis boom drainage holes.
Repetitive detailed or rotating probe inspections for
cracking in the drain holes on the lower skin panel in the center wing
box between frames 42 and 46 and corrective actions if necessary.
Corrective actions include repairing cracking and contacting the FAA or
EASA for repair and doing the repair.
Repetitive eddy current inspections for cracking of the
upper corner angle fitting and the vertical tee fitting at left and
right frame 40, and corrective actions if necessary. Corrective actions
include repairing, replacing the internal angle fitting and contacting
the FAA or EASA for repair and doing the repair.

You may obtain further information by examining the MCAI in the AD
docket.

Other Relevant Rulemaking

We are considering issuing three other NPRMs related to this NPRM:
Directorate Identifier 2010-NM-092-AD. That NPRM proposes
to supersede AD 98-26-01, amendment 39-10942 (63 FR 69179, December 16,
1998), to continue to require certain actions specified in that AD.
However, that NPRM does not restate paragraphs (p) and (r) of AD 98-26-
01. Instead, certain requirements of paragraphs (p) and (r) of that AD
are included in this NPRM, Directorate Identifier 2010-NM-090-AD.
Directorate Identifiers 2010-NM-089-AD and 2010-NM-091-AD.
Both of these NPRMs include the requirements of certain other
paragraphs of AD 98-26-01.

Relevant Service Information

Airbus has issued the service bulletins listed in the table that
follows:

Table--Service Information
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310-57- 01.......................... May 22, 2007.
2048.
Airbus Mandatory Service Bulletin A310-57- 02.......................... August 27, 2009.
2050, including Appendix 01.
Airbus Mandatory Service Bulletin A310-57- 02.......................... December 21, 2007.
2064, including Appendix 1.
----------------------------------------------------------------------------------------------------------------

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 44 products of U.S. registry. We also estimate that
it would take about 137 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $512,380, or $11,645 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

[[Page 52]]

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 adding the following new AD:

Airbus: Docket No. FAA-2010-1274; Directorate Identifier 2010-NM-
090-AD.

Comments Due Date

(a) We must receive comments by February 17, 2011.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A310-203, -204, -221, -222,
-304, -322, -324, and -325 airplanes, certificated in any category,
all serial numbers.

Subject

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

Reason

(e) The mandatory continuing airworthiness information (MCAI)
states:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France AD 1992-106-132(B) original issue up to revision 7 was issued
to require a set of inspection and modification tasks which
addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation
Regulation] 25-571 requirements related to damage-tolerance and
fatigue evaluation of structure. * * *.
* * * * *
The unsafe condition is reduced structural integrity of the wings.

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.

Cold Working of Trellis Boom Drainage Holes

(g) For Model A310-203, -204, -222, -304, -322 and -324
airplanes, except airplanes identified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD: Within the applicable time specified in Table
1 of this AD, cold work the trellis boom drainage holes, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007.
Certain compliance times specified in Table 1 of this AD are
applicable to short range use, average flight time (AFT) equal to or
less than 3.6 hours; or long range use, AFT exceeding 3.6 hours.

Table 1--Compliance Times for Paragraph (g) of This AD
------------------------------------------------------------------------

------------------------------------------------------------------------
Airplanes, as identified in Compliance time (whichever occurs later)
Airbus mandatory service
bulletin A310-57-2048,
revision 01, dated May 22,
2007
------------------------------------------------------------------------
Configuration 01 airplanes.. Prior to the Within 6 months
accumulation of after the effective
31,800 total flight date of this AD.
cycles or 63,600
total flight hours,
whichever occurs
first.
Configuration 02 airplanes.. Prior to the Within 6 months
accumulation of after the effective
40,000 total flight date of this AD.
cycles or 80,000
total flight hours,
whichever occurs
first.
Configuration 03 short range Prior to the Within 6 months
airplanes. accumulation of after the effective
30,950 total flight date of this AD.
cycles or 86,750
total flight hours,
whichever occurs
first.
Configuration 03 long range Prior to the Within 6 months
airplanes. accumulation of after the effective
24,100 total flight date of this AD.
cycles or 120,600
total flight hours,
whichever occurs
first.
------------------------------------------------------------------------

(1) Airplanes on which Airbus modification 06130 was done in
production.
(2) Airplanes on which Airbus Mandatory Service Bulletin A310-
57-2048 was done in service.
(3) Airplanes on which rework of cracked drain holes was done in
accordance with Airbus Mandatory Service Bulletin A310-57-2050.

Inspection of Trellis Boom Drainage Holes

(h) For all airplanes: Within the applicable intervals specified
in Table 2 of this AD, perform a detailed or rotating probe
inspection for cracking in the drain holes on the lower skin panel
in the center wing box between frames 42 and 46, in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-57-2050, Revision 02, dated August 27, 2009. Repeat the
inspections thereafter at intervals not to exceed the applicable
times specified in Table 3 of this AD. Certain compliance times
specified in Tables 2 and 3 of this AD are applicable to short range
use, average flight time (AFT) equal to or less than 3.6 hours; or
long range use, AFT exceeding 3.6 hours.

Table 2--Compliance Times for Paragraph (h) of This AD
------------------------------------------------------------------------

[[Page 53]]

Airplanes, as identified in Compliance time (whichever occurs later)
Airbus mandatory service
bulletin A310-57-2050,
revision 02, dated August
27, 2009
------------------------------------------------------------------------
Configuration 02 airplanes Within 32,850 flight Within 1,000 flight
on which Airbus Mandatory cycles or 65,700 cycles or 2,000
Service Bulletin A310-57- flight hours, flight hours,
2048 has been done within whichever occurs whichever occurs
the ``recommended'' first, after first, after the
compliance times specified accomplishing effective date of
in paragraph 1.E.(2), Airbus Mandatory this AD.
``Accomplishment Service Bulletin
Timescale,'' of Airbus A310-57-2048.
Mandatory Service Bulletin
A310-57-2048, Revision 01,
dated May 22, 2007.
Configuration 02 airplanes Within 8,600 flight Within 1,000 flight
on which Airbus Mandatory cycles or 17,250 cycles or 2,000
Service Bulletin A310-57- flight hours, flight hours,
2048 has not been done whichever occurs whichever occurs
within the ``recommended'' first, after first, after the
compliance times specified accomplishing the effective date of
in paragraph 1.E.(2), detailed inspection this AD.
``Accomplishment specified in Airbus
Timescale,'' of Airbus Mandatory Service
Mandatory Service Bulletin Bulletin A310-57-
A310-57-2048, Revision 01, 2048;
dated May 22, 2007. OR..................
Within 11,400 flight
cycles or 22,800
flight hours,
whichever occurs
first, after
accomplishing the
rotating probe
inspection
specified in Airbus
Mandatory Service
Bulletin A310-57-
2048.
Configuration 03 airplanes.. Prior to the Within 1,000 flight
accumulation of cycles or 2,000
22,300 total flight flight hours,
cycles or 44,550 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Configuration 04 airplanes.. Prior to the Within 1,000 flight
accumulation of cycles or 2,000
41,550 total flight flight hours,
cycles or 83,100 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Configuration 05 airplanes Prior to the Within 1,000 flight
on which Airbus Mandatory accumulation of cycles or 2,000
Service Bulletin A310-57- 40,000 total flight flight hours,
2048 has been done within cycles or 80,000 whichever occurs
the ``recommended'' total flight hours, first, after the
compliance times specified whichever occurs effective date of
in paragraph 1.E.(2), first. this AD.
``Accomplishment
Timescale,'' of Airbus
Mandatory Service Bulletin
A310-57-2048, Revision 01,
dated May 22, 2007.
Configuration 05 airplanes Within 10,600 flight Within 1,000 flight
on which Airbus Mandatory cycles or 21,150 cycles or 2,000
Service Bulletin A310-57- flight hours, flight hours,
2048 has not been done whichever occurs whichever occurs
within the ``recommended'' first, after first, after the
compliance times specified accomplishing the effective date of
in paragraph 1.E.(2), detailed inspection this AD.
``Accomplishment specified in Airbus
Timescale,'' of Airbus Mandatory Service
Mandatory Service Bulletin Bulletin A310-57-
A310-57-2048, Revision 01, 2048;
dated May 22, 2007. OR..................
Within 13,900 flight
cycles or 27,800
flight hours,
whichever occurs
first, after
accomplishing the
rotating probe
inspection
specified in Airbus
Mandatory Service
Bulletin A310-57-
2048.
Configuration 06 short range Prior to the Within 1,000 flight
airplanes. accumulation of cycles or 2,800
17,250 total flight flight hours,
cycles or 48,400 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Configuration 06 long range Prior to the Within 800 flight
airplanes. accumulation of cycles or 4,000
13,450 total flight flight hours,
cycles or 67,250 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Configuration 07 short range Prior to the Within 1,000 flight
airplanes. accumulation of cycles or 2,800
32,150 total flight flight hours,
cycles or 90,050 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Configuration 07 long range Prior to the Within 800 flight
airplanes. accumulation of cycles or 4,000
25,050 total flight flight hours,
cycles or 125,150 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Configuration 08 short range Prior to the Within 1,000 flight
airplanes on which Airbus accumulation of cycles or 2,800
Mandatory Service Bulletin 30,950 total flight flight hours,
A310-57-2048 has been done cycles or 86,750 whichever occurs
within the ``recommended'' total flight hours, first, after the
compliance times specified whichever occurs effective date of
in paragraph 1.E.(2), first. this AD.
``Accomplishment
Timescale,'' of Airbus
Mandatory Service Bulletin
A310-57-2048, Revision 01,
dated May 22, 2007.

[[Page 54]]

Table 3--Repetitive Intervals for Paragraph (h) of This AD, Depending on Most Recent Inspection Type
----------------------------------------------------------------------------------------------------------------
Airplanes, as identified in Airbus Type of inspection done
mandatory service bulletin A310-57-2050, during most recent Repetitive interval (not to exceed)
revision 02, dated August 27, 2009 inspection
----------------------------------------------------------------------------------------------------------------
Configuration 01 and 02 airplanes....... Detailed inspection........ 8,600 flight cycles or 17,250 flight
hours, whichever occurs first.
Rotating probe inspection.. 11,400 flight cycles or 22,800 flight
hours, whichever occurs first.
Configurations 03, 04, and 05 airplanes. Detailed inspection........ 10,600 flight cycles or 21,150 flight
hours, whichever occurs first.
Rotating probe inspection.. 13,900 flight cycles or 27,800 flight
hours, whichever occurs first.
Configurations 06, 07, and 08 short Detailed inspection........ 8,200 flight cycles or 23,000 flight
range airplanes. hours, whichever occurs first.
Rotating probe inspection.. 10,800 flight cycles or 30,300 flight
hours, whichever occurs first.
Configurations 06, 07, and 08 long range Detailed inspection........ 6,400 flight cycles or 31,950 flight
airplanes. hours, whichever occurs first.
Rotating probe inspection.. 8,400 flight cycles or 42,150 flight
hours, whichever occurs first.
----------------------------------------------------------------------------------------------------------------

Corrective Actions for Paragraph (h) of This AD

(i) If any cracking is found during any inspection required by
paragraph (h) of this AD, before further flight, do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2050,
Revision 02, dated August 27, 2009; except where the service
bulletin specifies to contact Airbus, before further flight, repair
in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
or EASA (or its delegated agent).

Inspection of Fuselage Frame 40 Upper Corner Fitting

(j) For all airplanes: Within the applicable time specified in
Table 4 of this AD, perform an eddy current inspection for cracking
of the upper corner fitting at left and right frame 40, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-57-2064, Revision 02, dated December 21, 2007.
Repeat the inspections thereafter at intervals not to exceed the
applicable times specified in Table 5 of this AD. Certain compliance
times specified in Tables 4 and 5 of this AD are applicable to short
range use, average flight time (AFT) equal to or less than 3.23
hours; or long range use, AFT exceeding 3.23 hours.

[[Page 55]]

Table 4--Compliance Times for Paragraph (j) of This AD
------------------------------------------------------------------------

------------------------------------------------------------------------
Airplane configurations Compliance time (whichever occurs later)
identified in Airbus
mandatory service bulletin
A310-57-2064, revision 02,
dated December 21, 2007
------------------------------------------------------------------------
Model A310-203, -204, -221, Prior to the Within 1,300 flight
and -222 airplanes accumulation of cycles or 2,700
identified as Configuration 15,100 total flight flight hours,
01. cycles or 30,300 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Model A310-203, -204, -221, Prior to the Within 1,300 flight
and -222 airplanes accumulation of cycles or 2,700
identified as 21,400 total flight flight hours,
Configurations 02 and 03. cycles or 42,800 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Model A310-304, -322, -324, Prior to the Within 600 flight
and -325 short range accumulation of cycles or 1,800
airplanes identified as 14,700 total flight flight hours,
Configuration 01. cycles or 41,300 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Model A310-304, -322, -324, Prior to the Within 600 flight
and -325 short range accumulation of cycles or 1,800
airplanes identified as 20,700 total flight flight hours,
Configurations 02 and 03. cycles or 58,300 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Model A310-304, -322, -324, Prior to the Within 500 flight
and -325 long range accumulation of cycles or 2,650
airplanes identified as 12,800 total flight flight hours,
Configuration 01. cycles or 64,000 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
Model A310-304, -322, -324, Prior to the Within 500 flight
and -325 long range accumulation of cycles or 2,650
airplanes identified as 18,000 total flight flight hours,
Configurations 02 and 03. cycles or 90,400 whichever occurs
total flight hours, first, after the
whichever occurs effective date of
first. this AD.
------------------------------------------------------------------------

Table 5--Repetitive Intervals for Paragraph (j) of This AD
------------------------------------------------------------------------
Repetitive interval (not to
Airplanes exceed)
------------------------------------------------------------------------
Model A310-203, -204, -221, and - 8,750 flight cycles or 17,550
222 airplanes. flight hours, whichever occurs
first.
Model A310-304, -322, -324, and - 5,800 flight cycles or 16,300
325 short range airplanes. flight hours, whichever occurs
first.
Model A310-304, -322, -324, and - 4,800 flight cycles or 24,050
325 long range airplanes. flight hours, whichever occurs
first.
------------------------------------------------------------------------

Corrective Actions for Paragraph (h) of This AD

(k) If, during any inspection required by paragraph (j) of this
AD, any crack is found, prior to further flight, do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2064,
Revision 02, dated December 21, 2007; except where the service
bulletin specifies to contact Airbus, before further flight, repair
in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
or EASA (or its delegated agent).

Credit for Actions Accomplished in Accordance With Previous Service
Information

(l) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2048, dated April
23, 1990, are considered acceptable for compliance with the
corresponding action specified in paragraph (g) of this AD.
(m) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2050, dated April
23, 1990; or Airbus Mandatory Service Bulletin A310-57-2050,
Revision 01, dated May 22, 2007; are considered acceptable for
compliance with the corresponding actions specified in paragraphs
(h) and (i) of this AD.
(n) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2064, dated August
24, 1995; or Revision 01, dated January 5, 2001; are acceptable for
compliance with the corresponding actions specified in paragraphs
(j) and (k) of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service
information as follows: No Differences.

Other FAA AD Provisions

(o) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information 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. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards 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.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.

Related Information

(p) Refer to MCAI EASA Airworthiness Directive 2009-0057, dated
March 13, 2009, and the service bulletins listed in Table 6 of this
AD, for related information.

Table 6--Service Information
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310-57- 01.......................... May 22, 2007.
2048.
Airbus Mandatory Service Bulletin A31-57- 02.......................... August 27, 2009.
2050.

[[Page 56]]

Airbus Mandatory Service Bulletin A310-57- 02.......................... December 21, 2007.
2064.
----------------------------------------------------------------------------------------------------------------

Issued in Renton, Washington on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-32992 Filed 12-30-10; 8:45 am]
BILLING CODE 4910-13-P

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