Airworthiness Directives; Airbus Model A310 Series Airplanes, 66659-66665 [2010-26659]

Download as PDF Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations a new airworthiness directive (AD), Amendment 39 16486, to read as follows: 2010–22–07 Eurocopter Deutschland GmbH: Amendment 39–16486; Docket No. FAA–2010–0780; Directorate Identifier 2009–SW–68–AD. Supersedes AD 2006–26–51, Amendment 39 14961, Docket No. FAA–2006–26721, Directorate Identifier 2006–SW–28–AD. Other Affected ADs (b) This AD supersedes AD 2006–26–51, Amendment 39–14961, Docket No. FAA 2006–26721, Directorate Identifier 2006–SW– 28–AD. Applicability (c) This AD applies to Model MBB–BK 117 C–2 helicopters with a tail rotor control lever B642M1009103, installed, certificated in any category. WReier-Aviles on DSKGBLS3C1PROD with RULES Reason (d) The mandatory continued airworthiness information (MCAI) AD states: ‘‘European Aviation Safety Agency (EASA) was informed by the manufacturer of an inflight incident in which a dynamic weight broke off the control lever subsequently leading to considerable vibrations. A visual inspection revealed that the threaded bolt of the control lever had broken off.’’ This AD requires actions that are intended to prevent separation of dynamic weights, severe vibration, and subsequent loss of control of the helicopter. Actions and Compliance (e) Before further flight, unless already done, mark the position of the weights, remove the split pins, remove the weights, and visually inspect the tail rotor control lever in the area around the split pin bore for score marks, notching, scratching, or a crack. Inspect by following the Accomplishment Instructions, paragraph 3.A.(1) through 3.A.(3) and Figure 1, of Eurocopter Alert Service Bulletin MBB BK 117 C–2–64A–002, Revision 2, dated August 6, 2007 (ASB). (1) If done previously, within the next 8 hours time-in-service (TIS) or before reaching 25 hours TIS after the last inspection, and thereafter at intervals not to exceed 8 hours TIS, repeat the visual inspection of the tail rotor control lever as required by paragraph (e) of this AD. (2) If you find a score mark, a notch, or a scratch that exceeds the maintenance manual limits, or find a crack, before further flight: (i) Replace the tail rotor control lever with an airworthy tail rotor control lever; and (ii) Reidentify the tail rotor head, head assembly, and drive system with the new part numbers by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB. (f) Within 100 hours TIS, unless already done, replace the control levers and reidentify the tail rotor head, head assembly, and drive system with the new part numbers 13:56 Oct 28, 2010 Jkt 223001 Differences Between the FAA AD and the MCAI AD (h) We refer to flight hours as hours TIS. We do not refer to a date of October 31, 2007, for replacing the levers because the date has passed. Effective Date (a) This airworthiness directive (AD) becomes effective on December 3, 2010. VerDate Mar<15>2010 by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB. (g) Replacing the control levers and reidentifying the part numbers is terminating action for the requirements of this AD. Other Information (i) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon Miles, ASW–111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222– 5122, fax (817) 222 5961, has the authority to approve AMOCs for this AD, if requested, using the procedures found in 14 CFR 39.19. (j) Special flight permits are prohibited. Related Information (k) MCAI EASA Airworthiness Directive No. 2006–0237, dated August 31, 2007, which supersedes EASA Emergency AD 2007–0189–E, dated July 12, 2007, contains related information. Joint Aircraft System/Component Code (l) The Joint Aircraft System/Component Code is 6400: Tail rotor system-control lever. Material Incorporated by Reference (m) The actions shall be done in accordance with the specified portions of Eurocopter Deutschland GmbH Alert Service Bulletin MBB BK117 C–2–64A–002, Revision 2, dated August 6, 2007. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or 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 Fort Worth, Texas, on October 12, 2010. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–26563 Filed 10–28–10; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 66659 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0680; Directorate Identifier 2008–NM–195–AD; Amendment 39–16482; AD 2010–22–03] 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. 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: Analysis performed in the frame of the Extended Service Goal has led Airbus to modify the inspection programme [modification of thresholds, intervals and associated configurations] which is currently ´ ´ required by DGAC (Direction Generale de l’Aviation Civile) France AD F–2005–001. This modified inspection programme is necessary to detect and prevent damage associated with a structural fatigue phenomenon of the rear spar internal angle and the tee fitting located in the centre wing box. This condition, if not corrected, could affect the structural integrity of the centre wing box. * * * * * 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 December 3, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 3, 2010. 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, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. E:\FR\FM\29OCR1.SGM 29OCR1 66660 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 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 July 13, 2010 (75 FR 39863), and proposed to supersede AD 2006– 09–05, Amendment 39–14575 (71 FR 25921, May 3, 2006). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Analysis performed in the frame of the Extended Service Goal has led Airbus to modify the inspection programme [modification of thresholds, intervals and associated configurations] which is currently ´ ´ required by DGAC (Direction Generale de l’Aviation Civile) France AD F–2005–001 [which corresponds to FAA AD 2006–09–05]. This modified inspection programme is necessary to detect and prevent damage associated with a structural fatigue phenomenon of the rear spar internal angle and the tee fitting located in the centre wing box. This condition, if not corrected, could affect the structural integrity of the centre wing box. For the reason stated above, this new EASA AD retains the requirements of DGAC France AD F–2005–001, which is superseded, and refers to the latest revision of Airbus Service Bulletin (SB) A310–57– 2047. The unsafe condition is reduced structural integrity of the wings. This AD retains the requirements of AD 2006–09–05, but with certain reduced compliance times. The required actions include doing repetitive rotating probe inspections for any crack of the rear spar internal angle and the left and right sides of the tee fitting, and doing related investigative/corrective actions if necessary. The actions also include modifying the holes in the internal angle and tee fitting by cold expansion. 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 received no comments on the NPRM or on the determination of the cost to the public. WReier-Aviles on DSKGBLS3C1PROD with RULES Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 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 Based on the service information, we estimate that this AD will affect about 66 products of U.S. registry. The actions that are required by AD 2006–09–05 and retained in this AD take up to 600 work-hours per product, at an average labor rate of $85 per work hour. Required parts cost up to $38,900 per product. Based on these figures, the estimated cost of the currently required actions is up to $89,900 per product. This new AD adds no new costs to affected operators; the manufacturer has modified the inspection program currently required by AD 2006–09–05. This AD reduces the compliance times required by the existing AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 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 removing Amendment 39–14575 (71 FR 25921, May 3, 2006) and adding the following new AD: ■ 2010–22–03 Airbus: Amendment 39–16482. Docket No. FAA–2010–0680; Directorate Identifier 2008–NM–195–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 3, 2010. Affected ADs (b) This AD supersedes AD 2006–09–05, Amendment 39–14575. This AD also affects certain requirements of AD 98–26–01, Amendment 39–10942. Applicability (c) This AD applies to all Airbus Model A310–203, –204, –221, –222, –304, –322, E:\FR\FM\29OCR1.SGM 29OCR1 66661 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations –324, and –325 airplanes, certificated in any category. affect the structural integrity of the centre wing box. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. * Reason (e) The mandatory continuing airworthiness information (MCAI) states: Analysis performed in the frame of the Extended Service Goal has led Airbus to modify the inspection programme [modification of thresholds, intervals and associated configurations] which is currently ´ ´ required by DGAC (Direction Generale de l’Aviation Civile) France AD F–2005–001 [which corresponds to FAA AD 2006–09–05]. This modified inspection programme is necessary to detect and prevent damage associated with a structural fatigue phenomenon of the rear spar internal angle and the tee fitting located in the centre wing box. This condition, if not corrected, could Compliance * * * * The unsafe condition is reduced structural integrity of the wings. (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. Restatement of Certain Requirements of AD 2006–09–05 Modification (g) For all airplanes except those that are modified by Airbus Modifications 06672S6812, 06673S6813, and 07387S7974 in production: Within 60 months after June 7, 2006 (the effective date of AD 2006–09– 05), modify the holes in the internal angle and tee fitting and do all applicable related investigative and corrective actions by accomplishing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A310–57–2035, Revision 08, dated September 19, 2005; or Airbus Mandatory Service Bulletin A310–57–2035, Revision 10, dated March 25, 2008; except as required by paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310–57–2035, Revision 10, dated March 25, 2008. Contact the FAA (h) Where the service information specified in Table 1 of this AD specifies to contact the manufacturer if certain cracks are found, before further flight, repair those conditions according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the ´ ´ Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent); or EASA (or its delegated agent). TABLE 1—SERVICE INFORMATION Document Revision Airbus Mandatory Service Bulletin A310–57–2035 .............................................................................................. Airbus Service Bulletin A310–57–2035 ................................................................................................................ Actions Accomplished According to Previous Issues of Airbus Service Bulletin A310–57–2035 (i) Actions accomplished before June 7, 2006, in accordance with the service Date 10 08 March 25, 2008. September 19, 2005. information specified in Table 2 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD. TABLE 2—PREVIOUS ISSUES OF SERVICE BULLETIN A310–57–2035 Document Airbus Airbus Airbus Airbus Airbus Airbus Airbus Service Service Service Service Service Service Service Bulletin Bulletin Bulletin Bulletin Bulletin Bulletin Bulletin A310–57–2035 A310–57–2035 A310–57–2035 A310–57–2035 A310–57–2035 A310–57–2035 A310–57–2035 .................................................................................................................. .................................................................................................................. .................................................................................................................. .................................................................................................................. .................................................................................................................. .................................................................................................................. .................................................................................................................. New Requirements of This AD—Revised Compliance Times for Inspections Required by AD 2006–09–05 WReier-Aviles on DSKGBLS3C1PROD with RULES Initial and Repetitive Inspections of the Rear Spar Internal Angle (j) For airplanes on which an inspection of the rear spar internal angle has not been done in accordance with Airbus Service Bulletin A310–57–2047 as of the effective date of this AD: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, do a rotating probe inspection for any crack of the rear spar internal angle located in the center wing box and do all applicable related investigative and corrective actions, in accordance with the Accomplishment VerDate Mar<15>2010 13:56 Oct 28, 2010 Revision Jkt 223001 Instructions of Airbus Service Bulletin A310– 57–2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 4 of this AD. Certain compliance times are applicable to short range use, average flight time (AFT) equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. Note 1: To establish the AFT, divide the accumulated flight time (counted from the take-off up to the landing) by the number of accumulated flight cycles. This gives the average flight time per flight cycle. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 1 2 3 4 5 6 7 Date October 13, 1989. February 26, 1990. May 23, 1990. April 15, 1992. May 27, 1992. March 8, 1994. April 17, 1996. (1) Within the applicable time specified in Table 3 of this AD. (2) Within the applicable time specified in paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: (i) For A310–203, –204, –221, and –222 airplanes: Within 700 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first. (ii) For A310–304, –322, –324, and –325 short range airplanes: Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first. (iii) For A310–304, –322, –324, and –325 long range airplanes: Within 500 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. E:\FR\FM\29OCR1.SGM 29OCR1 66662 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations TABLE 3—INITIAL INSPECTION INTERNAL ANGLE Model and configuration Compliance time (whichever occurs first) A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done. A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in production. A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 6,200 total flight cycles and 12,500 total flight hours. A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and are not done before the accumulation of 6,200 total flight cycles and 12,500 total flight hours. A310–304, –322, –324, and –325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done. A310–304, –322, –324, and –325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done. A310–304, –322, –324, and –325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done. A310–304, –322, –324, and –325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in production. A310–304, –322, –324, and –325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 4,700 total flight cycles and 13,100 total flight hours. A310–304, –322, –324, and –325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not done before the accumulation of 4,700 total flight cycles and 13,100 total flight hours. A310–304, –322, –324, and –325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 before the accumulation of 3,300 total flight cycles and 16,700 total flight hours. A310–304, –322, –324, and –325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not done before the accumulation of 3,300 total flight cycles and 16,700 total flight hours. Before the accumulation of 9,200 total flight cycles. Before the accumulation of 19,800 total flight cycles. Within 19,800 flight cycles after the effective date of this AD. Before the accumulation of 18,500 total flight hours. Before the accumulation of 39,600 total flight hours. Within 39,600 flight hours after the effective date of this AD. Within 8,200 flight cycles after the effective date of this AD. Within 16,400 flight hours after the effective date of this AD. Before the accumulation of 7,500 total flight cycles. Before the accumulation of 5,300 total flight cycles. Before the accumulation of 15,900 total flight cycles. Before the accumulation of 11,300 total flight cycles. Within 15,900 flight cycles after the effective date of this AD. Before the accumulation of 21,100 total flight hours. Before the accumulation of 26,900 total flight hours. Before the accumulation of 44,700 total flight hours. Before the accumulation of 56,900 total flight hours. Within 44,700 flight hours after the effective date of this AD. Within 8,500 flight cycles after the effective date of this AD. Within 23,800 flight hours after the effective date of this AD. Within 11,300 flight cycles after the effective date of this AD. Within 56,900 flight hours after the effective date of this AD. Within 6,000 flight cycles after the effective date of this AD. Within 30,300 flight hours after the effective date of this AD. TABLE 4—REPETITIVE INTERVALS Interval (not to exceed) A310–203, –204, –221, and –222 airplanes ............................................ A310–304, –322, –324, and –325 short range airplanes ........................ A310–304, –322, –324, and –325 long range airplanes ......................... WReier-Aviles on DSKGBLS3C1PROD with RULES Model and configuration Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first. Within 6,800 flight cycles or 19,100 flight hours, whichever occurs first. Within 4,800 flight cycles or 24,300 flight hours, whichever occurs first. (k) For airplanes on which an inspection of the rear spar internal angle has been done in accordance with Airbus Service Bulletin A310–57–2047 as of the effective date of this AD: At the applicable time specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, do a rotating probe inspection for any crack of the rear spar internal angle located in the center wing box and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310– 57–2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 4 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. (1) For A310–203, –204, –221, and –222 airplanes: At the earlier of the times specified VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD. (i) Within 7,940 flight cycles or 15,880 flight hours after the most recent inspection, whichever occurs first. (ii) At the later of the times specified in paragraphs (k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD. (A) Within the applicable interval specified in Table 4 of this AD. (B) Within 740 flight cycles or 1,480 flight hours after the effective date of this AD, whichever occurs first. (2) For A310–304, –322, –324, and –325 short range airplanes: At the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Within the applicable interval specified in Table 4 of this AD. (ii) Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first. (3) For A310–304, –322, –324, and –325 long range airplanes: At the later of the times PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 specified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD. (i) Within the applicable interval specified in Table 4 of this AD. (ii) Within 500 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. Initial and Repetitive Inspections of the Tee Fitting (l) For airplanes on which an inspection of the left and right sides of the tee fitting has not been done in accordance with Airbus Service Bulletin A310–57–2047 as of the effective date of this AD: At the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD, do a rotating probe inspection for any crack of the left and right sides of the tee fitting, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310– 57–2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) E:\FR\FM\29OCR1.SGM 29OCR1 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 6 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. (1) Within the applicable time specified in Table 5 of this AD. (2) Within the applicable time in paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD. (i) For A310–203, –204, –221, and –222 airplanes: Within 800 flight cycles or 1,600 flight hours, whichever occurs first. 66663 (ii) For A310–304, –322, –324, and –325 short range airplanes: Within 800 flight cycles or 2,200 flight hours, whichever occurs first. (iii) For A310–304, –322, –324, and –325 long range airplanes: Within 600 flight cycles or 3,100 flight hours, whichever occurs first. TABLE 5—INITIAL INSPECTION TEE FITTING Model and configuration Compliance time (whichever occurs first) A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 is not done. A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 is done in production. A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 8,100 total flight cycles and 16,200 total flight hours. A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310–57–2035 and not before the accumulation of 8,100 total flight cycles and 16,200 total flight hours. A310–304, –322, –324, and –325 short range airplanes on which Mod 6673S6813 is not done. A310–304, –322, –324, and –325 long range airplanes on which Mod 6673S6813 is not done. A310–304, –322, –324, and –325 short range airplanes on which Mod 6673S6813 is done in production. A310–304, –322, –324, and –325 long range airplanes on which Mod 6673S6813 is done in production. A310–304, –322, –324, and –325 short range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 5,800 total flight cycles and 16,400 total flight hours. A310–304, –322, –324, and –325 short range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310–57–2035 and not before the accumulation of 5,800 total flight cycles and 16,400 total flight hours. A310–304, –322, –324, and –325 long range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 4,600 total flight cycles and 23,100 total flight hours. A310–304, –322, –324, and –325 long range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310–57–2035 and not before the accumulation of 4,600 total flight cycles and 23,100 total flight hours. Before the accumulation of 14,300 flight cycles. Before the accumulation of 17,500 total flight cycles. Within 17,500 flight cycles after the effective date of this AD. Within 28,700 flight hours after the effective date of this AD. Before the accumulation of 35,000 total flight hours. Within 35,000 flight hours after the effective date of this AD. Within 9,600 flight cycles after the effective date of this AD. Within 19,200 flight hours after the effective date of this AD. Within 10,800 flight cycles after the effective date of this AD. Before the accumulation of 8,500 total flight cycles. Before the accumulation of 13,100 total flight cycles. Before the accumulation of 10,300 total flight cycles. Within 13,100 flight cycles after the effective date of this AD. Within 30,400 flight hours after the effective date of this AD. Before the accumulation of 42,800 total flight hours. Before the accumulation of 36,700 total flight hours. Before the accumulation of 51,600 total flight hours. Within 36,700 flight hours after the effective date of this AD. Within 7,400 flight cycles after the effective date of this AD. Within 20,900 flight hours after the effective date of this AD. Within 10,300 flight cycles after the effective date of this AD. Within 51,600 flight hours after the effective date of this AD. Within 6,000 flight cycles after the effective date of this AD. Within 30,300 flight hours after the effective date of this AD. TABLE 6—REPETITIVE INTERVALS Model and configuration Interval (not to exceed) A310–203, –204, –221, and –222 airplanes ................................................................................. 9,100 flight cycles or 18,300 flight hours, whichever occurs first. 7,300 flight cycles or 20,400 flight hours, whichever occurs first. 5,900 flight cycles or 29,600 flight hours, whichever occurs first. A310–304, –322, –324, and –325 short range airplanes .............................................................. WReier-Aviles on DSKGBLS3C1PROD with RULES A310–304, –322, –324, and –325 long range airplanes ............................................................... (m) For airplanes on which an inspection of the rear left and right sides of the tee fitting has been done in accordance with Airbus Service Bulletin A310–57–2047 as of the effective date of this AD: At the applicable time specified in paragraphs (m)(1) or (m)(2) of this AD, do a rotating probe inspection for any crack of the left and right sides of the tee fitting, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 Service Bulletin A310–57–2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 6 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 (1) For A310–203, –204, –221, and –222 airplanes: At the earlier of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD. (i) Within 10,800 flight cycles or 17,400 flight hours after the most recent inspection, whichever occurs first. (ii) At the later of the times specified in paragraphs (m)(1)(ii)(A) and (m)(1)(ii)(B) of this AD. (A) Within the applicable interval specified in Table 6 of this AD. E:\FR\FM\29OCR1.SGM 29OCR1 66664 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations specifies to contact the manufacturer if certain cracks are found, before further flight, repair those conditions according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent). (B) Within 700 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first. (2) For A310–304, –322, –324, and – 325 airplanes: At the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. (i) Within the applicable interval specified in Table 6 of this AD. (ii) Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first. No Reporting Required (o) Although Airbus Service Bulletin A310–57–2047, Revision 08, dated July 2, 2009, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (p) Actions accomplished before the effective date of this AD in accordance with Contact the FAA (n) Where Airbus Service Bulletin A310– 57–2047, Revision 08, dated July 2, 2009, Airbus Mandatory Service Bulletin A310–57– 2035, Revision 09, dated September 27, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD. (q) Actions accomplished before the effective date of this AD in accordance with the service information specified in Table 7 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraphs (j) through (m) of this AD. TABLE 7—PREVIOUS ISSUES OF AIRBUS SERVICE BULLETIN A310–57–2047 Document Airbus Airbus Airbus Airbus Airbus Service Service Service Service Service Bulletin Bulletin Bulletin Bulletin Bulletin A310–57–2047 A310–57–2047 A310–57–2047 A310–57–2047 A310–57–2047 Revision ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... Related AD (r) Accomplishing a rotating probe inspection of the rear spar internal angle and the tee fitting in accordance with Airbus Service Bulletin A310–57–2047, Revision 08, dated July 2, 2009, or a service bulletin listed in Table 7 of this AD, terminates the requirements specified in paragraph (o) of AD 98–26–01. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information tells you to contact the manufacturer for repair information, paragraph (n) of this AD requires that you contact the FAA or EASA (or its delegated agent) instead. Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (o) of this AD specifies that such submittal is not required. Other FAA AD Provisions (s) 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, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; 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) AMOCs approved previously in accordance with AD 2006–09–05, Amendment 39–14575, are approved as AMOCs for the corresponding provisions of this AD. (3) Airworthy Product: For any requirement in this AD to obtain corrective actions from Date 03 04 05 06 07 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 (t) Refer to MCAI EASA Airworthiness Directive 2008–0187, dated October 10, 2008; Airbus Service Bulletin A310–57–2047, Revision 08, dated July 2, 2009; and Airbus Mandatory Service Bulletin A310–57–2035, Revision 10, dated March 25, 2008; for related information. Material Incorporated by Reference (u) You must use Airbus Mandatory Service Bulletin A310–57–2035, Revision 10, dated March 25, 2008; and Airbus Service Bulletin A310–57–2047, Revision 08, dated July 2, 2009; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. Airbus Service Bulletin A310–57– 2047 contains the following effective pages: WReier-Aviles on DSKGBLS3C1PROD with RULES Page No. Revision level shown on page 1–7a, 26, 86, 88 ........................................................................................................................................... 7b–21, 26, 29–31, 33, 35, 38, 39, 44, 45, 95, 96 ........................................................................................ 22–25, 37 ..................................................................................................................................................... 27, 28, 36, 47–56, 61–74 ............................................................................................................................. 32, 34, 40–43, 59–60, 81–85, 87, 89–94 .................................................................................................... 46, 75–80 ..................................................................................................................................................... 57, 58 ........................................................................................................................................................... 08 ................ 07 ................ 06 ................ Original ........ 04 ................ 05 ................ 2 .................. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 (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 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 November 26, 1997. March 5, 1999. August 3, 2000. July 13, 2004. March 14, 2008. Date shown on page July 2, 2009. March 14, 2008. July 13, 2004. February 26, 1991. March 5, 1999. August 3, 2000. January 22, 1997. 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 E:\FR\FM\29OCR1.SGM 29OCR1 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 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 October 13, 2010. John Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–26659 Filed 10–28–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE INTERIOR Bureau of Ocean Energy Management, Regulation, and Enforcement 5. On the same page, in the same table, in the same column, in the seventh row from the bottom of the page, the blank entry should read ‘‘ONRR.’’ 6. On page 61072, in the table, in the third column, in the 22nd row, the blank entry should read ‘‘§ 1206.111’’. 7. On page 61073, in the table, in the third column, in the 16th row, ‘‘Associate Director’’ should read ‘‘Director’’. PART 1208—SALE OF FEDERAL ROYALTY OIL [CORRECTED] 8. On page 61081, in the table, in the third column, in the first row, ‘‘§ 208.8(a)’’ should read ‘‘§ 1208.8(a)’’. 9. On the same page, in the same table, in the same column, in the fifth row, ‘‘§ 208.7(g)’’ should read ‘‘§ 1208.7(g)’’. [FR Doc. C1–2010–24721 Filed 10–28–10; 8:45 am] BILLING CODE 4310–MR–W–P 30 CFR Parts 201, 202, 203, 204, 206, 207, 208, 210, 212, 217, 218, 219, 220, 227, 228, 229, 241, 243, and 290 DEPARTMENT OF EDUCATION Office of Natural Resources Revenue RIN 1840–AD04 34 CFR Part 600 [Docket ID ED–2010–OPE–0012] 30 CFR Parts 1201, 1202, 1203, 1204, 1206, 1207, 1208, 1210, 1212, 1217, 1218, 1219, 1220, 1227, 1228, 1229, 1241, 1243, and 1290 Program Integrity: Gainful Employment—New Programs Office of Postsecondary Education, Department of Education. ACTION: Final regulations. AGENCY: [Docket No. MMS–2010–MRM–0033] RIN 1010–AD70 In rule document 2010–24721 beginning on page 61051 in the issue of Monday, October 4, 2010, make the following corrections: WReier-Aviles on DSKGBLS3C1PROD with RULES PART 1206—PRODUCT VALUATION [CORRECTED] 13:56 Oct 28, 2010 Jkt 223001 These regulations are effective July 1, 2011. However, affected parties do not have to comply with the information collection requirements in § 600.20(d) until the Department of Education publishes in the Federal Register the control number assigned by the Office of Management and Budget (OMB) to these information collection requirements. Publication of the control number notifies the public that OMB has approved these information collection requirements under the Paperwork Reduction Act of 1995. FOR FURTHER INFORMATION CONTACT: John Kolotos or Fred Sellers. Telephone: (202) 502–7762 or (202) 502–7502, or via the Internet at: John.Kolotos@ed.gov or Fred.Sellers@ed.gov. DATES: 1. On page 61070, in the table, in the first column, in the fourth row, ‘‘§ 1206.52(c)(2)’’ should read ‘‘§ 1206.52(c)(2)(i)’’. 2. On the same page, in the same table, in the same column, in the eleventh row, ‘‘§ 1206.53(e)(5) two times’’ should read ‘‘1206.52(e)(5) two times’’. 3. On the same page, in the same table, in the same column, in both the fifteenth and sixteenth rows, ‘‘§ 1206.52(c) introductory text’’ should read ‘‘§ 1206.53(c) introductory text’’. 4. On page 61071, in the table, in the third column, in the eighteenth row from the bottom of the page, ‘‘part 207’’ should read ‘‘part 1207.’’ VerDate Mar<15>2010 The Secretary amends the regulations for Institutional Eligibility Under the Higher Education Act of 1965, as amended (HEA), to establish a process under which an institution applies for approval to offer an educational program that leads to gainful employment in a recognized occupation. SUMMARY: Reorganization of Title 30, Code of Federal Regulations PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 66665 If you use a telecommunications device for the deaf (TDD), call the Federal Relay Service (FRS), toll free, at 1–800–877–8339. Individuals with disabilities can obtain this document in an accessible format (e.g., braille, large print, audiotape, or computer diskette) on request to one of the contact persons listed under FOR FURTHER INFORMATION CONTACT. On July 26, 2010, the Secretary published a notice of proposed rulemaking (NPRM) for gainful employment issues in the Federal Register (75 FR 43616). In the preamble to the NPRM, the Secretary discussed on pages 43617 through 43624 the major regulations proposed in that document to establish measures for determining whether certain programs lead to gainful employment in recognized occupations and the conditions under which those programs remain eligible for title IV, HEA program funds. In these final regulations, we address in a limited way only one issue from the proposed regulations: The provisions relating to the Secretary’s approval of additional programs. The remaining issues will be addressed in final regulations that we intend to publish in the next few months. SUPPLEMENTARY INFORMATION: Implementation Date of These Regulations Section 482(c) of the HEA requires that regulations affecting programs under title IV of the HEA be published in final form by November 1 prior to the start of the award year (July 1) to which they apply. However, that section also permits the Secretary to designate any regulation as one that an entity subject to the regulation may choose to implement earlier and to specify the conditions under which the entity may implement the provisions early. The Secretary has not designated any of the provisions in these final regulations for early implementation. Analysis of Comments and Changes These final regulations were developed through the use of negotiated rulemaking. Section 492 of the HEA requires that, before publishing any proposed regulations to implement programs under title IV of the HEA, the Secretary must obtain public involvement in the development of the proposed regulations. After obtaining advice and recommendations, the Secretary must conduct a negotiated rulemaking process to develop the proposed regulations. The negotiated rulemaking committee did not reach E:\FR\FM\29OCR1.SGM 29OCR1

Agencies

[Federal Register Volume 75, Number 209 (Friday, October 29, 2010)]
[Rules and Regulations]
[Pages 66659-66665]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-26659]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0680; Directorate Identifier 2008-NM-195-AD; 
Amendment 39-16482; AD 2010-22-03]
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:

    Analysis performed in the frame of the Extended Service Goal has 
led Airbus to modify the inspection programme [modification of 
thresholds, intervals and associated configurations] which is 
currently required by DGAC (Direction G[eacute]n[eacute]rale de 
l'Aviation Civile) France AD F-2005-001.
    This modified inspection programme is necessary to detect and 
prevent damage associated with a structural fatigue phenomenon of 
the rear spar internal angle and the tee fitting located in the 
centre wing box. This condition, if not corrected, could affect the 
structural integrity of the centre wing box.
* * * * *
    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 December 3, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 3, 
2010.

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, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

[[Page 66660]]


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 July 13, 2010 (75 FR 
39863), and proposed to supersede AD 2006-09-05, Amendment 39-14575 (71 
FR 25921, May 3, 2006). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:

    Analysis performed in the frame of the Extended Service Goal has 
led Airbus to modify the inspection programme [modification of 
thresholds, intervals and associated configurations] which is 
currently required by DGAC (Direction G[eacute]n[eacute]rale de 
l'Aviation Civile) France AD F-2005-001 [which corresponds to FAA AD 
2006-09-05].
    This modified inspection programme is necessary to detect and 
prevent damage associated with a structural fatigue phenomenon of 
the rear spar internal angle and the tee fitting located in the 
centre wing box. This condition, if not corrected, could affect the 
structural integrity of the centre wing box.
    For the reason stated above, this new EASA AD retains the 
requirements of DGAC France AD F-2005-001, which is superseded, and 
refers to the latest revision of Airbus Service Bulletin (SB) A310-
57-2047.

    The unsafe condition is reduced structural integrity of the wings. 
This AD retains the requirements of AD 2006-09-05, but with certain 
reduced compliance times. The required actions include doing repetitive 
rotating probe inspections for any crack of the rear spar internal 
angle and the left and right sides of the tee fitting, and doing 
related investigative/corrective actions if necessary. The actions also 
include modifying the holes in the internal angle and tee fitting by 
cold expansion. 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 received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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

    Based on the service information, we estimate that this AD will 
affect about 66 products of U.S. registry.
    The actions that are required by AD 2006-09-05 and retained in this 
AD take up to 600 work-hours per product, at an average labor rate of 
$85 per work hour. Required parts cost up to $38,900 per product. Based 
on these figures, the estimated cost of the currently required actions 
is up to $89,900 per product.
    This new AD adds no new costs to affected operators; the 
manufacturer has modified the inspection program currently required by 
AD 2006-09-05. This AD reduces the compliance times required by the 
existing AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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

0
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 removing Amendment 39-14575 (71 FR 
25921, May 3, 2006) and adding the following new AD:

2010-22-03 Airbus: Amendment 39-16482. Docket No. FAA-2010-0680; 
Directorate Identifier 2008-NM-195-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
3, 2010.

Affected ADs

    (b) This AD supersedes AD 2006-09-05, Amendment 39-14575. This 
AD also affects certain requirements of AD 98-26-01, Amendment 39-
10942.

Applicability

    (c) This AD applies to all Airbus Model A310-203, -204, -221, -
222, -304, -322,

[[Page 66661]]

-324, and -325 airplanes, certificated in any category.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Analysis performed in the frame of the Extended Service Goal has 
led Airbus to modify the inspection programme [modification of 
thresholds, intervals and associated configurations] which is 
currently required by DGAC (Direction G[eacute]n[eacute]rale de 
l'Aviation Civile) France AD F-2005-001 [which corresponds to FAA AD 
2006-09-05].
    This modified inspection programme is necessary to detect and 
prevent damage associated with a structural fatigue phenomenon of 
the rear spar internal angle and the tee fitting located in the 
centre wing box. This condition, if not corrected, could affect the 
structural integrity of the centre wing box.
* * * * *
    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.

Restatement of Certain Requirements of AD 2006-09-05

Modification

    (g) For all airplanes except those that are modified by Airbus 
Modifications 06672S6812, 06673S6813, and 07387S7974 in production: 
Within 60 months after June 7, 2006 (the effective date of AD 2006-
09-05), modify the holes in the internal angle and tee fitting and 
do all applicable related investigative and corrective actions by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Airbus Service Bulletin A310-57-2035, Revision 08, 
dated September 19, 2005; or Airbus Mandatory Service Bulletin A310-
57-2035, Revision 10, dated March 25, 2008; except as required by 
paragraph (h) of this AD. Do all applicable related investigative 
and corrective actions before further flight. As of the effective 
date of this AD, use only Airbus Mandatory Service Bulletin A310-57-
2035, Revision 10, dated March 25, 2008.

Contact the FAA

    (h) Where the service information specified in Table 1 of this 
AD specifies to contact the manufacturer if certain cracks are 
found, before further flight, repair those conditions according to a 
method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent); or EASA (or its delegated agent).

                      Table 1--Service Information
------------------------------------------------------------------------
            Document              Revision              Date
------------------------------------------------------------------------
Airbus Mandatory Service                10  March 25, 2008.
 Bulletin A310-57-2035.
Airbus Service Bulletin A310-57-        08  September 19, 2005.
 2035.
------------------------------------------------------------------------

Actions Accomplished According to Previous Issues of Airbus Service 
Bulletin A310-57-2035

    (i) Actions accomplished before June 7, 2006, in accordance with 
the service information specified in Table 2 of this AD, are 
considered acceptable for compliance with the corresponding actions 
specified in paragraph (g) of this AD.

        Table 2--Previous Issues of Service Bulletin A310-57-2035
------------------------------------------------------------------------
            Document               Revision              Date
------------------------------------------------------------------------
Airbus Service Bulletin A310-57-          1  October 13, 1989.
 2035.
Airbus Service Bulletin A310-57-          2  February 26, 1990.
 2035.
Airbus Service Bulletin A310-57-          3  May 23, 1990.
 2035.
Airbus Service Bulletin A310-57-          4  April 15, 1992.
 2035.
Airbus Service Bulletin A310-57-          5  May 27, 1992.
 2035.
Airbus Service Bulletin A310-57-          6  March 8, 1994.
 2035.
Airbus Service Bulletin A310-57-          7  April 17, 1996.
 2035.
------------------------------------------------------------------------

New Requirements of This AD--Revised Compliance Times for Inspections 
Required by AD 2006-09-05

Initial and Repetitive Inspections of the Rear Spar Internal Angle

    (j) For airplanes on which an inspection of the rear spar 
internal angle has not been done in accordance with Airbus Service 
Bulletin A310-57-2047 as of the effective date of this AD: At the 
later of the times specified in paragraphs (j)(1) and (j)(2) of this 
AD, do a rotating probe inspection for any crack of the rear spar 
internal angle located in the center wing box and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, 
Revision 08, dated July 2, 2009; except as required by paragraphs 
(n) and (o) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspection 
thereafter at the applicable time specified in Table 4 of this AD. 
Certain compliance times are applicable to short range use, average 
flight time (AFT) equal to or less than 4 hours, or long range use, 
AFT exceeding 4 hours.

    Note 1: To establish the AFT, divide the accumulated flight time 
(counted from the take-off up to the landing) by the number of 
accumulated flight cycles. This gives the average flight time per 
flight cycle.

    (1) Within the applicable time specified in Table 3 of this AD.
    (2) Within the applicable time specified in paragraph (j)(2)(i), 
(j)(2)(ii), or (j)(2)(iii) of this AD:
    (i) For A310-203, -204, -221, and -222 airplanes: Within 700 
flight cycles or 1,500 flight hours after the effective date of this 
AD, whichever occurs first.
    (ii) For A310-304, -322, -324, and -325 short range airplanes: 
Within 700 flight cycles or 1,900 flight hours after the effective 
date of this AD, whichever occurs first.
    (iii) For A310-304, -322, -324, and -325 long range airplanes: 
Within 500 flight cycles or 2,500 flight hours after the effective 
date of this AD, whichever occurs first.

[[Page 66662]]



                                   Table 3--Initial Inspection Internal Angle
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
Model and configuration                                       Compliance time (whichever occurs first)
----------------------------------------------------------------------------------------------------------------
A310-203, -204, -221, and -222 airplanes on which   Before the accumulation of     Before the accumulation of
 Mod 6672S6812 and Mod 7387S7974 are not done.       9,200 total flight cycles.     18,500 total flight hours.
A310-203, -204, -221, and -222 airplanes on which   Before the accumulation of     Before the accumulation of
 Mod 6672S6812 and Mod 7387S7974 are done in         19,800 total flight cycles.    39,600 total flight hours.
 production.
A310-203, -204, -221, and -222 airplanes on which   Within 19,800 flight cycles    Within 39,600 flight hours
 Mod 6672S6812 and Mod 7387S7974 are done in         after the effective date of    after the effective date of
 accordance with Airbus Service Bulletin A310-57-    this AD.                       this AD.
 2035 and before the accumulation of 6,200 total
 flight cycles and 12,500 total flight hours.
A310-203, -204, -221, and -222 airplanes on which   Within 8,200 flight cycles     Within 16,400 flight hours
 Mod 6672S6812 and Mod 7387S7974 are done in         after the effective date of    after the effective date of
 accordance with Airbus Service Bulletin A310-57-    this AD.                       this AD.
 2035 and are not done before the accumulation of
 6,200 total flight cycles and 12,500 total flight
 hours.
A310-304, -322, -324, and -325 short range          Before the accumulation of     Before the accumulation of
 airplanes on which Mod 6672S6812 and Mod            7,500 total flight cycles.     21,100 total flight hours.
 7387S7974 are not done.
A310-304, -322, -324, and -325 long range           Before the accumulation of     Before the accumulation of
 airplanes on which Mod 6672S6812 and Mod            5,300 total flight cycles.     26,900 total flight hours.
 7387S7974 are not done.
A310-304, -322, -324, and -325 short range          Before the accumulation of     Before the accumulation of
 airplanes on which Mod 6672S6812 and Mod            15,900 total flight cycles.    44,700 total flight hours.
 7387S7974 are done.
A310-304, -322, -324, and -325 long range           Before the accumulation of     Before the accumulation of
 airplanes on which Mod 6672S6812 and Mod            11,300 total flight cycles.    56,900 total flight hours.
 7387S7974 are done in production.
A310-304, -322, -324, and -325 short range          Within 15,900 flight cycles    Within 44,700 flight hours
 airplanes on which Mod 6672S6812 and Mod            after the effective date of    after the effective date of
 7387S7974 are done in accordance with Airbus        this AD.                       this AD.
 Service Bulletin A310-57-2035 and before the
 accumulation of 4,700 total flight cycles and
 13,100 total flight hours.
A310-304, -322, -324, and -325 short range          Within 8,500 flight cycles     Within 23,800 flight hours
 airplanes on which Mod 6672S6812 and Mod            after the effective date of    after the effective date of
 7387S7974 are done in accordance with Airbus        this AD.                       this AD.
 Service Bulletin A310-57-2035 and not done before
 the accumulation of 4,700 total flight cycles and
 13,100 total flight hours.
A310-304, -322, -324, and -325 long range           Within 11,300 flight cycles    Within 56,900 flight hours
 airplanes on which Mod 6672S6812 and Mod            after the effective date of    after the effective date of
 7387S7974 are done in accordance with Airbus        this AD.                       this AD.
 Service Bulletin A310-57-2035 before the
 accumulation of 3,300 total flight cycles and
 16,700 total flight hours.
A310-304, -322, -324, and -325 long range           Within 6,000 flight cycles     Within 30,300 flight hours
 airplanes on which Mod 6672S6812 and Mod            after the effective date of    after the effective date of
 7387S7974 are done in accordance with Airbus        this AD.                       this AD.
 Service Bulletin A310-57-2035 and not done before
 the accumulation of 3,300 total flight cycles and
 16,700 total flight hours.
----------------------------------------------------------------------------------------------------------------


                      Table 4--Repetitive Intervals
------------------------------------------------------------------------
        Model and configuration              Interval (not to exceed)
------------------------------------------------------------------------
A310-203, -204, -221, and -222           Within 7,200 flight cycles or
 airplanes.                               14,400 flight hours, whichever
                                          occurs first.
A310-304, -322, -324, and -325 short     Within 6,800 flight cycles or
 range airplanes.                         19,100 flight hours, whichever
                                          occurs first.
A310-304, -322, -324, and -325 long      Within 4,800 flight cycles or
 range airplanes.                         24,300 flight hours, whichever
                                          occurs first.
------------------------------------------------------------------------

    (k) For airplanes on which an inspection of the rear spar 
internal angle has been done in accordance with Airbus Service 
Bulletin A310-57-2047 as of the effective date of this AD: At the 
applicable time specified in paragraphs (k)(1), (k)(2), and (k)(3) 
of this AD, do a rotating probe inspection for any crack of the rear 
spar internal angle located in the center wing box and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-57-2047, Revision 08, dated July 2, 2009; except as 
required by paragraphs (n) and (o) of this AD. Do all applicable 
related investigative and corrective actions before further flight. 
Repeat the inspection thereafter at the applicable time specified in 
Table 4 of this AD. Certain compliance times are applicable to short 
range use, AFT equal to or less than 4 hours, or long range use, AFT 
exceeding 4 hours.
    (1) For A310-203, -204, -221, and -222 airplanes: At the earlier 
of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of 
this AD.
    (i) Within 7,940 flight cycles or 15,880 flight hours after the 
most recent inspection, whichever occurs first.
    (ii) At the later of the times specified in paragraphs 
(k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD.
    (A) Within the applicable interval specified in Table 4 of this 
AD.
    (B) Within 740 flight cycles or 1,480 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For A310-304, -322, -324, and -325 short range airplanes: At 
the later of the times specified in paragraphs (k)(2)(i) and 
(k)(2)(ii) of this AD.
    (i) Within the applicable interval specified in Table 4 of this 
AD.
    (ii) Within 700 flight cycles or 1,900 flight hours after the 
effective date of this AD, whichever occurs first.
    (3) For A310-304, -322, -324, and -325 long range airplanes: At 
the later of the times specified in paragraphs (k)(3)(i) and 
(k)(3)(ii) of this AD.
    (i) Within the applicable interval specified in Table 4 of this 
AD.
    (ii) Within 500 flight cycles or 2,500 flight hours after the 
effective date of this AD, whichever occurs first.

Initial and Repetitive Inspections of the Tee Fitting

    (l) For airplanes on which an inspection of the left and right 
sides of the tee fitting has not been done in accordance with Airbus 
Service Bulletin A310-57-2047 as of the effective date of this AD: 
At the later of the times specified in paragraphs (l)(1) and (l)(2) 
of this AD, do a rotating probe inspection for any crack of the left 
and right sides of the tee fitting, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, 
Revision 08, dated July 2, 2009; except as required by paragraphs 
(n) and (o)

[[Page 66663]]

of this AD. Do all applicable related investigative and corrective 
actions before further flight. Repeat the inspection thereafter at 
the applicable time specified in Table 6 of this AD. Certain 
compliance times are applicable to short range use, AFT equal to or 
less than 4 hours, or long range use, AFT exceeding 4 hours.
    (1) Within the applicable time specified in Table 5 of this AD.
    (2) Within the applicable time in paragraph (l)(2)(i), 
(l)(2)(ii), or (l)(2)(iii) of this AD.
    (i) For A310-203, -204, -221, and -222 airplanes: Within 800 
flight cycles or 1,600 flight hours, whichever occurs first.
    (ii) For A310-304, -322, -324, and -325 short range airplanes: 
Within 800 flight cycles or 2,200 flight hours, whichever occurs 
first.
    (iii) For A310-304, -322, -324, and -325 long range airplanes: 
Within 600 flight cycles or 3,100 flight hours, whichever occurs 
first.

                                     Table 5--Initial Inspection Tee Fitting
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
              Model and configuration                         Compliance time (whichever occurs first)
----------------------------------------------------------------------------------------------------------------
A310-203, -204, -221, and -222 airplanes on which   Before the accumulation of     Within 28,700 flight hours
 Mod 6673S6813 is not done.                          14,300 flight cycles.          after the effective date of
                                                                                    this AD.
A310-203, -204, -221, and -222 airplanes on which   Before the accumulation of     Before the accumulation of
 Mod 6673S6813 is done in production.                17,500 total flight cycles.    35,000 total flight hours.
A310-203, -204, -221, and -222 airplanes on which   Within 17,500 flight cycles    Within 35,000 flight hours
 Mod 6673S6813 is done in accordance with Airbus     after the effective date of    after the effective date of
 Service Bulletin A310-57-2035 and before the        this AD.                       this AD.
 accumulation of 8,100 total flight cycles and
 16,200 total flight hours.
A310-203, -204, -221, and -222 airplanes on which   Within 9,600 flight cycles     Within 19,200 flight hours
 Mod 6673S6813 is done in accordance with Airbus     after the effective date of    after the effective date of
 Service Bulletin A310-57-2035 and not before the    this AD.                       this AD.
 accumulation of 8,100 total flight cycles and
 16,200 total flight hours.
A310-304, -322, -324, and -325 short range          Within 10,800 flight cycles    Within 30,400 flight hours
 airplanes on which Mod 6673S6813 is not done.       after the effective date of    after the effective date of
                                                     this AD.                       this AD.
A310-304, -322, -324, and -325 long range           Before the accumulation of     Before the accumulation of
 airplanes on which Mod 6673S6813 is not done.       8,500 total flight cycles.     42,800 total flight hours.
A310-304, -322, -324, and -325 short range          Before the accumulation of     Before the accumulation of
 airplanes on which Mod 6673S6813 is done in         13,100 total flight cycles.    36,700 total flight hours.
 production.
A310-304, -322, -324, and -325 long range           Before the accumulation of     Before the accumulation of
 airplanes on which Mod 6673S6813 is done in         10,300 total flight cycles.    51,600 total flight hours.
 production.
A310-304, -322, -324, and -325 short range          Within 13,100 flight cycles    Within 36,700 flight hours
 airplanes on which Mod 6673S6813 is done in         after the effective date of    after the effective date of
 accordance with Airbus Service Bulletin A310-57-    this AD.                       this AD.
 2035 and before the accumulation of 5,800 total
 flight cycles and 16,400 total flight hours.
A310-304, -322, -324, and -325 short range          Within 7,400 flight cycles     Within 20,900 flight hours
 airplanes on which Mod 6673S6813 is done in         after the effective date of    after the effective date of
 accordance with Airbus Service Bulletin A310-57-    this AD.                       this AD.
 2035 and not before the accumulation of 5,800
 total flight cycles and 16,400 total flight hours.
A310-304, -322, -324, and -325 long range           Within 10,300 flight cycles    Within 51,600 flight hours
 airplanes on which Mod 6673S6813 is done in         after the effective date of    after the effective date of
 accordance with Airbus Service Bulletin A310-57-    this AD.                       this AD.
 2035 and before the accumulation of 4,600 total
 flight cycles and 23,100 total flight hours.
A310-304, -322, -324, and -325 long range           Within 6,000 flight cycles     Within 30,300 flight hours
 airplanes on which Mod 6673S6813 is done in         after the effective date of    after the effective date of
 accordance with Airbus Service Bulletin A310-57-    this AD.                       this AD.
 2035 and not before the accumulation of 4,600
 total flight cycles and 23,100 total flight hours.
----------------------------------------------------------------------------------------------------------------


                                          Table 6--Repetitive Intervals
----------------------------------------------------------------------------------------------------------------
         Model and configuration                                  Interval (not to exceed)
----------------------------------------------------------------------------------------------------------------
A310-203, -204, -221, and -222 airplanes.  9,100 flight cycles or 18,300 flight hours, whichever occurs first.
A310-304, -322, -324, and -325 short       7,300 flight cycles or 20,400 flight hours, whichever occurs first.
 range airplanes.
A310-304, -322, -324, and -325 long range  5,900 flight cycles or 29,600 flight hours, whichever occurs first.
 airplanes.
----------------------------------------------------------------------------------------------------------------

     (m) For airplanes on which an inspection of the rear left and 
right sides of the tee fitting has been done in accordance with 
Airbus Service Bulletin A310-57-2047 as of the effective date of 
this AD: At the applicable time specified in paragraphs (m)(1) or 
(m)(2) of this AD, do a rotating probe inspection for any crack of 
the left and right sides of the tee fitting, and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, 
Revision 08, dated July 2, 2009; except as required by paragraphs 
(n) and (o) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspection 
thereafter at the applicable time specified in Table 6 of this AD. 
Certain compliance times are applicable to short range use, AFT 
equal to or less than 4 hours, or long range use, AFT exceeding 4 
hours.
    (1) For A310-203, -204, -221, and -222 airplanes: At the earlier 
of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of 
this AD.
    (i) Within 10,800 flight cycles or 17,400 flight hours after the 
most recent inspection, whichever occurs first.
    (ii) At the later of the times specified in paragraphs 
(m)(1)(ii)(A) and (m)(1)(ii)(B) of this AD.
    (A) Within the applicable interval specified in Table 6 of this 
AD.

[[Page 66664]]

    (B) Within 700 flight cycles or 1,500 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For A310-304, -322, -324, and - 325 airplanes: At the later 
of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of 
this AD.
    (i) Within the applicable interval specified in Table 6 of this 
AD.
    (ii) Within 700 flight cycles or 1,900 flight hours after the 
effective date of this AD, whichever occurs first.

Contact the FAA

    (n) Where Airbus Service Bulletin A310-57-2047, Revision 08, 
dated July 2, 2009, specifies to contact the manufacturer if certain 
cracks are found, before further flight, repair those conditions 
according to a method approved by either the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or 
its delegated agent).

No Reporting Required

    (o) Although Airbus Service Bulletin A310-57-2047, Revision 08, 
dated July 2, 2009, specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.
    (p) Actions accomplished before the effective date of this AD in 
accordance with Airbus Mandatory Service Bulletin A310-57-2035, 
Revision 09, dated September 27, 2007, are considered acceptable for 
compliance with the corresponding actions specified in paragraph (g) 
of this AD.
    (q) Actions accomplished before the effective date of this AD in 
accordance with the service information specified in Table 7 of this 
AD, are considered acceptable for compliance with the corresponding 
actions specified in paragraphs (j) through (m) of this AD.

                        Table 7--Previous Issues of Airbus Service Bulletin A310-57-2047
----------------------------------------------------------------------------------------------------------------
                    Document                        Revision                           Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A310-57-2047...........              03  November 26, 1997.
Airbus Service Bulletin A310-57-2047...........              04  March 5, 1999.
Airbus Service Bulletin A310-57-2047...........              05  August 3, 2000.
Airbus Service Bulletin A310-57-2047...........              06  July 13, 2004.
Airbus Service Bulletin A310-57-2047...........              07  March 14, 2008.
----------------------------------------------------------------------------------------------------------------

Related AD

    (r) Accomplishing a rotating probe inspection of the rear spar 
internal angle and the tee fitting in accordance with Airbus Service 
Bulletin A310-57-2047, Revision 08, dated July 2, 2009, or a service 
bulletin listed in Table 7 of this AD, terminates the requirements 
specified in paragraph (o) of AD 98-26-01.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows:
    Although the MCAI or service information tells you to contact 
the manufacturer for repair information, paragraph (n) of this AD 
requires that you contact the FAA or EASA (or its delegated agent) 
instead.
    Although the MCAI or service information tells you to submit 
information to the manufacturer, paragraph (o) of this AD specifies 
that such submittal is not required.

Other FAA AD Provisions

    (s) 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, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; 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) AMOCs approved previously in accordance with AD 2006-09-05, 
Amendment 39-14575, are approved as AMOCs for the corresponding 
provisions of this AD.
    (3) 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

    (t) Refer to MCAI EASA Airworthiness Directive 2008-0187, dated 
October 10, 2008; Airbus Service Bulletin A310-57-2047, Revision 08, 
dated July 2, 2009; and Airbus Mandatory Service Bulletin A310-57-
2035, Revision 10, dated March 25, 2008; for related information.

Material Incorporated by Reference

    (u) You must use Airbus Mandatory Service Bulletin A310-57-2035, 
Revision 10, dated March 25, 2008; and Airbus Service Bulletin A310-
57-2047, Revision 08, dated July 2, 2009; as applicable; to do the 
actions required by this AD, unless the AD specifies otherwise. 
Airbus Service Bulletin A310-57-2047 contains the following 
effective pages:

----------------------------------------------------------------------------------------------------------------
                Page No.                  Revision level shown on page             Date shown on page
----------------------------------------------------------------------------------------------------------------
1-7a, 26, 86, 88........................  08..........................  July 2, 2009.
7b-21, 26, 29-31, 33, 35, 38, 39, 44,     07..........................  March 14, 2008.
 45, 95, 96.
22-25, 37...............................  06..........................  July 13, 2004.
27, 28, 36, 47-56, 61-74................  Original....................  February 26, 1991.
32, 34, 40-43, 59-60, 81-85, 87, 89-94..  04..........................  March 5, 1999.
46, 75-80...............................  05..........................  August 3, 2000.
57, 58..................................  2...........................  January 22, 1997.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of this 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

[[Page 66665]]

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 October 13, 2010.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-26659 Filed 10-28-10; 8:45 am]
BILLING CODE 4910-13-P