Airworthiness Directives; Airbus Model A310 Series Airplanes, 27227-27232 [2011-10685]

Download as PDF 27227 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations TABLE 9—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Service Bulletin Revision Airbus Service Bulletin A310–57–2038 ....................................................................................................... Airbus Service Bulletin A310–57–2046 ....................................................................................................... Airbus Service Bulletin A310–57–2046, Change Notice 4A ....................................................................... 2 ................... 4 ................... Original ......... (3) For service information identified in this 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.airwortheas@airbus.com; Internet https:// www.airbus.com. (4) You may review copies of the 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. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on April 22, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–10684 Filed 5–10–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1274; Directorate Identifier 2010–NM–090–AD; Amendment 39–16687; AD 2011–10–06] Airworthiness Directives; Airbus Model A310 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: srobinson on DSKHWCL6B1PROD with RULES ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) * * * VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 * * * * * The unsafe condition is reduced structural integrity of the wings. We are issuing this AD to require actions to correct the unsafe condition on these products. This AD becomes effective June 15, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 15, 2011. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. 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: DATES: Discussion RIN 2120–AA64 SUMMARY: 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. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on January 3, 2011 (76 FR 50). That NPRM proposed 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 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 [European Aviation Safety Agency] published AD 2007–0053, which replaced DGAC France AD F–1992–106–132R7. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Date January 4, 1996. October 16, 1996. October 16, 1996. 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. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Revise Paragraph Header An anonymous commenter requested that the paragraph reference in the paragraph header between table 5 and paragraph (k) of the NPRM be revised from ‘‘paragraph (h)’’ to ‘‘paragraph (j)’’. The commenter believed the intent was to reference paragraph (j) of the NPRM. We agree with the commenter’s request. We have revised the paragraph header between table 5 and paragraph (k) of this AD. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously. We determined that this change will not E:\FR\FM\11MYR1.SGM 11MYR1 27228 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations increase the economic burden on any operator or increase the scope of the AD. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a Note within the AD. Costs of Compliance We estimate that this AD will affect 44 products of U.S. registry. We also estimate that it will take about 137 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 AD: 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 AD and placed it in the AD docket. 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 the NPRM, 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 adding the following new AD: ■ 2011–10–06 Airbus: Amendment 39–16687. Docket No. FAA–2010–1274; Directorate Identifier 2010–NM–090–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 15, 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 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. 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. srobinson on DSKHWCL6B1PROD with RULES 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 ................................. VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 Compliance time (whichever occurs later) Prior to the accumulation of 31,800 total flight cycles or 63,600 total flight hours, whichever occurs first. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Within 6 months after the effective date of this AD. E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27229 TABLE 1—COMPLIANCE TIMES FOR PARAGRAPH (g) OF THIS AD—Continued 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. 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. 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 Airplanes, as identified in Airbus Mandatory Service Bulletin A310–57–2050, Revision 02, dated August 27, 2009 Configuration 01 airplanes ................................. 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 ................................. srobinson on DSKHWCL6B1PROD with RULES 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. VerDate Mar<15>2010 16:21 May 10, 2011 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. 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 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. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 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 2,000 flight hours, whichever occurs first, after the effective date of this AD. E:\FR\FM\11MYR1.SGM 11MYR1 27230 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations TABLE 2—COMPLIANCE TIMES FOR PARAGRAPH (h) OF THIS AD—Continued Configuration 06 short range airplanes .............. Configuration 06 long range airplanes ............... Configuration 07 short range airplanes .............. 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. 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. 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 2,800 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. 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 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD. 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 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 ............. 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. 10,800 flight cycles or 30,300 flight hours, whichever occurs first. 6,400 flight cycles or 31,950 flight hours, whichever occurs first. Rotating probe inspection .. srobinson on DSKHWCL6B1PROD with RULES Configurations 03, 04, and 05 airplanes .......................... Detailed inspection ............. Rotating probe inspection .. Configurations 06, 07, and 08 short range airplanes ....... Detailed inspection ............. Rotating probe inspection .. Configurations 06, 07, and 08 long range airplanes ........ VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 PO 00000 Detailed inspection ............. Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27231 TABLE 3—REPETITIVE INTERVALS FOR PARAGRAPH (h) OF THIS AD, DEPENDING ON MOST RECENT INSPECTION TYPE— Continued Airplanes, as identified in Airbus Mandatory Service Bulletin A310–57–2050, Revision 02, dated August 27, 2009 (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 Repetitive interval (not to exceed) Rotating probe inspection .. Corrective Actions for Paragraph (h) of This AD Type of inspection done during most recent inspection 8,400 flight cycles or 42,150 flight hours, whichever occurs first. accordance with a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or European Aviation Safety Agency (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. 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 RULES Corrective Actions for Paragraph (j) of This AD ANM–116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent). (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, 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 VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 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, Airbus Mandatory Service Bulletin A310–57–2064, Revision 01, dated January 5, 2001; are acceptable for compliance with the corresponding actions specified in paragraphs (j) and (k) of this AD. E:\FR\FM\11MYR1.SGM 11MYR1 27232 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations Flight Standards District Office, as appropriate, or 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 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. 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local (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 (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 A310–57–2050 ........................................................................................... Airbus Mandatory Service Bulletin A310–57–2064 ........................................................................................... Material Incorporated by Reference (q) You must use the applicable service information contained in Table 7 of this AD 01 02 02 Date May 22, 2007. August 27, 2009. December 21, 2007. to do the actions required by this AD, unless the AD specifies otherwise. TABLE 7—ALL MATERIAL INCORPORATED BY REFERENCE Service Bulletin Revision Airbus Mandatory Service Bulletin A310–57–2048 ........................................................................................... Airbus Mandatory Service Bulletin A310–57–2050, excluding Appendix 01 .................................................... Airbus Mandatory Service Bulletin A310–57–2064, excluding Appendix 1 ...................................................... srobinson on DSKHWCL6B1PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference of the service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this 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.airwortheas@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on April 22, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–10685 Filed 5–10–11; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1276; Directorate Identifier 2010–NM–092–AD; Amendment 39–16689; AD 2011–10–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede two existing ADs. This 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: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) * * * PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 01 02 02 Date May 22, 2007. August 27, 2009. December 21, 2007. has been issued in order to mandate a set of inspections/modifications which address 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, fuselage, and stabilizers. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 15, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 15, 2011. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 20, 1999 (63 FR 69179, December 16, 1998). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. E:\FR\FM\11MYR1.SGM 11MYR1

Agencies

[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Rules and Regulations]
[Pages 27227-27232]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-10685]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1274; Directorate Identifier 2010-NM-090-AD; 
Amendment 39-16687; AD 2011-10-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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. We 
are issuing this AD to require actions to correct the unsafe condition 
on these products.

DATES: This AD becomes effective June 15, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 15, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on January 3, 2011 (76 
FR 50). That NPRM proposed 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 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 [European 
Aviation Safety Agency] 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Revise Paragraph Header

    An anonymous commenter requested that the paragraph reference in 
the paragraph header between table 5 and paragraph (k) of the NPRM be 
revised from ``paragraph (h)'' to ``paragraph (j)''. The commenter 
believed the intent was to reference paragraph (j) of the NPRM.
    We agree with the commenter's request. We have revised the 
paragraph header between table 5 and paragraph (k) of this AD.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the change described previously. We determined that this change 
will not

[[Page 27228]]

increase the economic burden on any operator or increase the scope of 
the AD.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect 44 products of U.S. registry. 
We also estimate that it will take about 137 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    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 AD and placed it in the AD docket.

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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2011-10-06 Airbus: Amendment 39-16687. Docket No. FAA-2010-1274; 
Directorate Identifier 2010-NM-090-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 15, 
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) * * * 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.

[[Page 27229]]

 
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
------------------------------------------------------------------------
 
------------------------------------------------------------------------
 Airplanes, as identified in   Compliance time (whichever occurs later)
  Airbus Mandatory Service
   Bulletin A310-57-2050,
  Revision 02, dated August
          27, 2009
------------------------------------------------------------------------
Configuration 01 airplanes..  Prior to the          Within 1,000 flight
                               accumulation of       cycles or 2,000
                               17,800 total flight   flight hours,
                               cycles or 35,600      whichever occurs
                               total flight hours,   first, after the
                               whichever occurs      effective date of
                               first.                this AD.
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.

[[Page 27230]]

 
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.
Configuration 08 short range  Within 8,200 flight   Within 1,000 flight
 airplanes on which Airbus     cycles or 23,000      cycles or 2,800
 Mandatory Service Bulletin    flight hours,         flight hours,
 A310-57-2048 has not been     whichever occurs      whichever occurs
 done within the               first, after          first, after the
 ``recommended'' compliance    accomplishing the     effective date of
 times specified in            detailed inspection   this AD.
 paragraph 1.E.(2),            specified in Airbus
 ``Accomplishment              Mandatory Service
 Timescale,'' of Airbus        Bulletin A310-57-
 Mandatory Service Bulletin    2048;
 A310-57-2048, Revision 01,   OR..................
 dated May 22, 2007.          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.
Configuration 08 long range   Prior to the          Within 800 flight
 airplanes on which Airbus     accumulation of       cycles or 4,000
 Mandatory Service Bulletin    24,100 total flight   flight hours,
 A310-57-2048 has been done    cycles or 120,600     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.
Configuration 08 long range   Within 6,400 flight   Within 800 flight
 airplanes on which Airbus     cycles or 31,950      cycles or 4,000
 Mandatory Service Bulletin    flight hours,         flight hours,
 A310-57-2048 has not been     whichever occurs      whichever occurs
 done within the               first, after          first, after the
 ``recommended'' compliance    accomplishing the     effective date of
 times specified in            detailed inspection   this AD.
 paragraph 1.E.(2),            specified in Airbus
 ``Accomplishment              Mandatory Service
 Timescale,'' of Airbus        Bulletin A310-57-
 Mandatory Service Bulletin    2048;
 A310-57-2048, Revision 01,   OR..................
 dated May 22, 2007.          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.
------------------------------------------------------------------------


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

[[Page 27231]]

 
                                Rotating probe     8,400 flight cycles
                                 inspection.        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 European Aviation Safety Agency (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.

         Table 4--Compliance Times for Paragraph (j) of This AD
------------------------------------------------------------------------
 
------------------------------------------------------------------------
   Airplane configurations                  Compliance time
    identified in Airbus               (whichever occurs later)
 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 -222     8,750 flight cycles or 17,550
 airplanes.                               flight hours, whichever occurs
                                          first.
Model A310-304, -322, -324, and -325     5,800 flight cycles or 16,300
 short range airplanes.                   flight hours, whichever occurs
                                          first.
Model A310-304, -322, -324, and -325     4,800 flight cycles or 24,050
 long range airplanes.                    flight hours, whichever occurs
                                          first.
------------------------------------------------------------------------

Corrective Actions for Paragraph (j) 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, Airbus Mandatory Service Bulletin A310-57-2064, 
Revision 01, dated January 5, 2001; are acceptable for compliance 
with the corresponding actions specified in paragraphs (j) and (k) 
of this AD.

[[Page 27232]]

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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate, or 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 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

    (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                 01  May 22, 2007.
 Bulletin A310-57-2048.
Airbus Mandatory Service                 02  August 27, 2009.
 Bulletin A310-57-2050.
Airbus Mandatory Service                 02  December 21, 2007.
 Bulletin A310-57-2064.
------------------------------------------------------------------------

Material Incorporated by Reference

    (q) You must use the applicable service information contained in 
Table 7 of this AD to do the actions required by this AD, unless the 
AD specifies otherwise.

             Table 7--All Material Incorporated by Reference
------------------------------------------------------------------------
       Service Bulletin           Revision               Date
------------------------------------------------------------------------
Airbus Mandatory Service                 01  May 22, 2007.
 Bulletin A310-57-2048.
Airbus Mandatory Service                 02  August 27, 2009.
 Bulletin A310-57-2050,
 excluding Appendix 01.
Airbus Mandatory Service                 02  December 21, 2007.
 Bulletin A310-57-2064,
 excluding Appendix 1.
------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the 
incorporation by reference of the service information under 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) For service information identified in this 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.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-10685 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P