Airworthiness Directives; Airbus Model A310 Series Airplanes, 29874-29879 [E7-10028]

Download as PDF cprice-sewell on PRODPC61 with RULES 29874 Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations relative for issuance of an immigrant visa under section 204(a) of the Act. (When more than one petition is submitted by the same petitioner on behalf of orphans who are brothers or sisters, only one fee will be required.)— $670. Form I–600A. For filing an application for advance processing of orphan petition. (When more than one petition is submitted by the same petitioner on behalf of orphans who are brothers or sisters, only one fee will be required.)—$670. No fee is charged if Form I–600 has not yet been submitted in connection with an approved Form I– 600A if a written request from the applicant for an extension of the approval has been received by USCIS prior to the expiration date of approval indicated on the Form I–171H. 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For filing an application for a certificate of citizenship under section 309(c) or section 341 of the Act—$460, for applications filed on behalf of a biological child and $420 for applications filed on behalf of an adopted child. Form N–600K. For filing an application for citizenship and issuance of certificate under section 322 of the PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 Act—$460, for an application filed on behalf of a biological child and $420 for an application filed on behalf of an adopted child. * * * * * (c) * * * (5) No fee relating to any application, petition, appeal, motion, or request made to United States Citizenship and Immigration Services may be waived under paragraph (c)(1) of this section except for the following: Biometrics; Form I–90; Form I–485 (only in the case of an alien in lawful nonimmigrant status under sections 101(a)(15)(T) or (U) of the Act; an applicant under section 209(b) of the Act; an approved self-petitioning battered or abused spouse, parent, or child of a United States citizen or lawful permanent resident; or an alien to whom section 212(a)(4) of the Act does not apply with respect to adjustment of status); Form I– 751; Form I–765; Form I–817; Form N– 300; Form N–336; Form N–400; Form N–470; Form N–565; Form N–600; Form N–600K; and Form I–290B and motions filed with United States Citizenship and Immigration Services relating to the specified forms in this paragraph (c). * * * * * Dated: May 3, 2007. Michael Chertoff, Secretary. [FR Doc. E7–10371 Filed 5–29–07; 8:45 am] BILLING CODE 4410–10–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–26857; Directorate Identifier 2006–NM–126–AD; Amendment 39–15069; AD 2007–11–12] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A310 series airplanes. That AD currently requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also currently E:\FR\FM\30MYR1.SGM 30MYR1 Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations provides for optional terminating action for certain inspections. This new AD retains all requirements of the existing AD, mandates the previously optional terminating action, and reduces the applicability of the existing AD. This AD results from a determination that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings. We are issuing this AD to prevent corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings. DATES: This AD becomes effective July 5, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 5, 2007. On September 4, 1998 (63 FR 40819, July 31, 1998), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 98–16–06, amendment 39–10682 (63 FR 40819, July 31, 1998). The existing AD applies to all Airbus Model A310 series airplanes. That NPRM was published in the Federal Register on January 19, 2007 (72 FR 2464). That NPRM proposed to retain the requirements of AD 98–16–06. These requirements are inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That NPRM also proposed to mandate the previously optional terminating action, and reduce the applicability of the existing AD. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Give Credit for Previous Inspections FedEx concurs with the NPRM, but requests that we give credit for previous inspections (initial and repetitive) accomplished in accordance with AD 98–16–06. FedEx points out that this credit should be given for actions in paragraphs (f), (g), and (l) of the NPRM. We partially agree with the request. We agree that it is necessary for the AD to give credit for inspections accomplished previously in accordance with AD 98–16–06. We disagree that it is necessary to change the AD in this regard. Paragraph (e) of the AD states, 29875 ‘‘You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.’’ Therefore, the AD already gives credit for required actions that were accomplished according to AD 98–16– 06. Explanation of New Service Information Airbus has issued Service Bulletin A310–53–2037, Revision 03, including Appendix 01, dated July 26, 2006. We referred in the NPRM to Service Bulletin A310–53–2037, Revision 1, dated April 29, 1992; and Revision 02, dated November 27, 2000; as the appropriate source of service information for accomplishing certain actions. Revision 03 of the service bulletin updates the effectivity and improves the inspection and repair procedures. Revision 03 states that no additional work is required for airplanes modified in accordance with Revision 02 or any previous revision. We have changed Table 1 in paragraph (n) of this AD to refer to Revision 03 for accomplishing certain required actions, and we have changed Table 3 in paragraph (p) of this AD to give credit to operators who accomplished the actions in accordance with Revision 02 of the service bulletin. Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate per work hour is $80. ESTIMATED COSTS Number of U.S.registered airplanes cprice-sewell on PRODPC61 with RULES Action Work hours Parts Cost per airplane Repetitive inspections behind scuff plates (required by AD 98– 16–06). Repetitive inspections of corner doublers, failsafe ring, and door frames (required by AD 98–16–06). 26 ................................. None ............................. $2,080 .......................... 46 $95,680. Between 4 and 100 depending on kit purchased. None ............................. Between $320 and $8,000. 46 Between $14,720, and $368,000 per inspection cycle. VerDate Aug<31>2005 15:13 May 29, 2007 Jkt 211001 PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 E:\FR\FM\30MYR1.SGM 30MYR1 Fleet cost 29876 Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations ESTIMATED COSTS—Continued Action Terminating modification for repetitive inspection of corner doublers, fail-safe ring, and door frames. Work hours Between 8 and 55 depending on kit purchased. 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. cprice-sewell on PRODPC61 with RULES Regulatory Findings We have 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate Aug<31>2005 Parts 15:13 May 29, 2007 Jkt 211001 Cost per airplane Between $506 and $6,098 depending on kit purchased. Between $1,146 and $10,498. 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–10682 (63 FR 40819, July 31, 1998) and by adding the following new airworthiness directive (AD): I 2007–11–12 Airbus: Amendment 39–15069. Docket No. FAA–2007–26857; Directorate Identifier 2006–NM–126–AD. Effective Date (a) This AD becomes effective July 5, 2007. Affected ADs (b) This AD supersedes AD 98–16–06. Applicability (c) This AD applies to Airbus Model A310 series airplanes; certificated in any category; excluding those airplanes on which Airbus Modifications 5068, 7201, and 7298 have been incorporated in production. Unsafe Condition (d) This AD results from a determination that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings. We are issuing this AD to prevent corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. PO 00000 Frm 00040 Fmt 4700 Number of U.S.registered airplanes Sfmt 4700 46 Fleet cost Between $52,716 and $482,908. Requirements of AD 98–16–06 Initial Inspection Behind Scuff Plates and Repair if Necessary With Revised Affected Doors (f) Perform an initial inspection of the areas behind the scuff plates below the passenger/ crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A310–53–2030, Revision 5, dated March 6, 1991, at the applicable time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If any crack or corrosion is found during this inspection, prior to further flight, repair in accordance with the service bulletin. Accomplishment of this inspection is not required for the aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have been accomplished: Perform the initial inspection within 9 years since airplane manufacture, or within 1 year after September 4, 1998 (the effective date of AD 98–16–06), whichever occurs later. (2) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have not been accomplished, and on which the procedures described in Airbus Service Bulletin A310–53–2004, Revision 2, dated June 17, 1985; or Airbus Service Information Letter 53–033, Revision 2, dated November 23, 1984; have been accomplished: Perform the initial inspection within 5 years since airplane manufacture, or within 1 year after September 4, 1998, whichever occurs later. (3) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have not been accomplished, and on which the procedures described in Airbus Service Bulletin A310–53–2004, Revision 2, dated June 17, 1985; or Airbus Service Information Letter 53–033, Revision 2, dated November 23, 1984; have not been accomplished: Perform the initial inspection within 4 years since airplane manufacture, or within 1 year after September 4, 1998, whichever occurs later. Repetitive Inspections Behind Scuff Plates (g) Perform repetitive inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A310–53–2041, Revision 02, dated July 2, 1996, at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Accomplishment of these inspections is not required for the aft passenger/crew doors if E:\FR\FM\30MYR1.SGM 30MYR1 Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations a steel doubler that covers the entire inspection area is installed. (1) For the forward passenger/crew doors, the bulk cargo door, and the aft passenger/ crew doors, except the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler, on all Model A310–200 and –300 series airplanes: Perform the first inspection within 5 years after accomplishing the inspection required by paragraph (f) of this AD; and repeat the inspection thereafter at intervals not to exceed 5 years. (2) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew door on all Model A310–200 series airplanes: Perform the first inspection within 5 years or 12,000 landings after accomplishing the inspection required by paragraph (f) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 12,000 landings, whichever occurs first. (3) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew door on all Model A310–300 series airplanes: Perform the first inspection within 5 years or 7,000 landings after accomplishing the inspection required by paragraph (f) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 7,000 landings, whichever occurs first. Repair of Scuff Plates if Necessary (h) If any crack is found during any inspection required by paragraph (g) or (n) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A310–53–2041, Revision 02, dated July 2, 1996. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (i) If any corrosion is found during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A310–53–2041, Revision 02, dated July 2, 1996. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. (1) For Model A310–200 series airplanes: Inspect at intervals not to exceed 5 years or 9,600 landings, whichever occurs first. (2) For Model A310–300 series airplanes: Inspect at intervals not to exceed 5 years or 5,600 landings, whichever occurs first. (j) Accomplishment of the actions required by paragraph (g), (h), or (i) of this AD in accordance with Airbus Service Bulletin A310–53–2041, dated December 5, 1990; or Revision 01, dated March 6, 1991; prior to September 4, 1998, is acceptable for compliance with that paragraph. Initial Inspection of Corner Doublers, FailSafe Ring, and Door Frames (k) Perform an inspection to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the left- and right-hand forward, mid, and aft passenger/crew door structures, in accordance with Airbus Service Bulletin A310–53–2037, Revision 1, dated April 29, 1992, and at the applicable times specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (1) For the upper corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 2,000 landings after September 4, 1998, whichever occurs later. (2) For the lower corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later. (3) For the upper and lower corners of the aft doors, and for the parts underneath the corners of the upper door frames: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later. Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door Frames (l) Repeat the inspections required by paragraph (k) of this AD at the applicable times specified in paragraphs (l)(1), (l)(2), (l)(3), (l)(4), and (l)(5). (1) For the upper corners of the forward doors: Inspect at intervals not to exceed 6,000 landings. 29877 (2) For the lower corners of the forward doors: Inspect at intervals not to exceed 10,000 landings. (3) For the upper and lower corners of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using a ROTO test technique: Inspect at intervals not to exceed 8,000 landings. (4) For the upper and lower corners of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using an x-ray technique: Inspect at intervals not to exceed 3,500 landings. (5) For the areas around the fasteners in the vicinity of stringer 12 on the upper door frames of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using a visual technique: Inspect at intervals not to exceed 6,900 landings. Repair of Corner Doublers, Fail-Safe Ring, and/or Door Frames if Necessary (m) If any crack is found during any inspection required by paragraph (k) or (l) of this AD: Prior to further flight, accomplish the requirement of paragraph (m)(1) or (m)(2) of this AD, as applicable. (1) If any crack is found, and the crack can be eliminated using the method specified in Airbus Service Bulletin A310–53–2037, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000: Prior to further flight, repair the crack in accordance with that service bulletin. (2) If any crack is found, and the crack cannot be eliminated using the method specified in Airbus Service Bulletin A310– 53–2037, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000: Prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate. New Requirements of This AD New Revision of Service Bulletins (n) As of the effective date of this AD, use only the service bulletins specified in Table 1 of this AD. TABLE 1.—NEW REVISION OF SERVICE BULLETINS Do the action(s) required by— In accordance with the accomplishment instructions of Airbus Service Bulletin— (1) Paragraph (f) of this AD ...................................................................... (2) Paragraph (k) and (m)(1) of this AD ................................................... A310–53–2030, Revision 06, dated July 2, 1996. A310–53–2037, Revision 03, excluding Appendix 01, dated July 26, 2006. cprice-sewell on PRODPC61 with RULES Terminating Modification for Repetitive Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (o) Modify the passenger/crew door structures in accordance with the VerDate Aug<31>2005 15:13 May 29, 2007 Jkt 211001 Accomplishment Instructions of Airbus Service Bulletin A310–53–2017, Revision 09, dated May 17, 2004. Do the modification at the applicable time in paragraph (o)(1) or (o)(2) of Table 2 of this AD. Accomplishment PO 00000 Frm 00041 Fmt 4700 Sfmt 4700 of this modification constitutes terminating action for the repetitive inspections required by paragraph (l) of this AD. The inspections required by paragraph (f) of this AD must be done before accomplishing this modification. E:\FR\FM\30MYR1.SGM 30MYR1 29878 Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations TABLE 2.—COMPLIANCE TIME FOR TERMINATING MODIFICATION For model— Compliance time (1) A310–203, –204, –221, and –222 airplanes ...................................... Before the accumulation of 40,000 flight cycles since the date of issuance of the original French standard Airworthiness Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later. Before the accumulation of 35,000 flight cycles since the date of issuance of the original French standard Airworthiness Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later. (2) A310–304, –322, –324, and –325 airplanes ...................................... Earlier Revision of Service Bulletins (p) Actions done before the effective date of this AD in accordance with the service bulletins identified in Table 3 of this AD are acceptable for compliance with the corresponding requirements of this AD. TABLE 3.—EARLIER REVISION(S) OF SERVICE BULLETINS Revision level Airbus Service Bulletin (1) A310–53–2017 ........................................................................................................................................... (2) A310–53–2017 ........................................................................................................................................... (3) A310–53–2037 ........................................................................................................................................... Alternative Methods of Compliance (AMOCs) (q)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Alternative methods of compliance, approved previously in accordance with AD 98–16–06 are approved as alternative methods of compliance with the corresponding provisions of paragraphs (f) through (m) of this AD. (3) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. 07 08 02 Date February 25, 1992. September 7, 2000. November 27, 2000. Related Information (r) French airworthiness directives 1991– 132–124(B) R1, dated November 29, 2000, and F–2004–103, dated July 7, 2004, also address the subject of this AD. Material Incorporated by Reference (s) You must use the service information listed in Table 4 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 4.—ALL MATERIAL INCORPORATED BY REFERENCE Revision level Airbus Service Bulletin A310–53–2017 ................................................................................................................................................. A310–53–2030 ................................................................................................................................................. A310–53–2030 ................................................................................................................................................. A310–53–2037 ................................................................................................................................................. A310–53–2037, excluding Appendix 01 .......................................................................................................... A310–53–2037, excluding Appendix 01 .......................................................................................................... A310–53–2041 ................................................................................................................................................. (1) The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 5 of this AD 09 5 06 1 02 03 02 Date May 17, 2004. March 6, 1991. July 2, 1996. April 29, 1992. November 27, 2000. July 26, 2006. July 2, 1996. in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 5.—NEW MATERIAL INCORPORATED BY REFERENCE Revision level cprice-sewell on PRODPC61 with RULES Airbus Service Bulletin A310–53–2017 ................................................................................................................................................. A310–53–2030 ................................................................................................................................................. A310–53–2037 ................................................................................................................................................. A310–53–2037, excluding Appendix 01 .......................................................................................................... A310–53–2037, excluding Appendix 01 .......................................................................................................... VerDate Aug<31>2005 15:13 May 29, 2007 Jkt 211001 PO 00000 Frm 00042 Fmt 4700 Sfmt 4700 E:\FR\FM\30MYR1.SGM 09 06 1 02 03 30MYR1 Date May 17, 2004. July 2, 1996. April 29, 1992. November 27, 2000. July 26, 2006. Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations 29879 Airbus Service Bulletin A310–53–2037, Revision 1, dated April 29, 1992, contains the following effective pages: Page No. Revision level shown on page 1, 4, 6, 11–15, 18, 29, 39–44, 46, 57 ................................... 2, 3, 5, 7–10, 16, 17, 19–28, 30–38, 45,47–56, 58–60 ....... Revision 1 ............................................................................ Original ................................................................................. (2) On September 4, 1998 (63 FR 40819, July 31, 1998), the Director of the Federal Register approved the incorporation by Date shown on page April 29, 1992. December 11, 1990. reference of the service information listed in Table 6 of this AD. TABLE 6.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Revision level Airbus Service Bulletin A310–53–2030 .......................................................................................................................................................... A310–53–2041 .......................................................................................................................................................... (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Renton, Washington, on May 15, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10028 Filed 5–29–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27494; Directorate Identifier 2006–NM–269–AD; Amendment 39–15071; AD 2007–11–14] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135BJ Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: cprice-sewell on PRODPC61 with RULES VerDate Aug<31>2005 15:13 May 29, 2007 Jkt 211001 It has been found that both fuel level control units (LCU) and their associated harnesses throughout the aircraft does not comply with the requirements of proper segregation, in order to preclude a possible ignition source in the vicinity of the fuel tanks, as required by SFAR (Special Federal Aviation Regulation) 88 regulations. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 5, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 5, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington. Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Streamlined Issuance of AD 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 SUMMARY: product. The MCAI describes the unsafe condition as: The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register PO 00000 Frm 00043 Fmt 4700 Sfmt 4700 5 02 Date March 6, 1991. July 2, 1996. requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD contains text copied from the MCAI and for this reason might not follow our plain language principles. 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 March 8, 2007 (72 FR 10429). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: It has been found that both fuel level control units (LCU) and their associated harnesses throughout the aircraft does not comply with the requirements of proper segregation, in order to preclude a possible ignition source in the vicinity of the fuel tanks, as required by SFAR (Special Federal Aviation Regulation) 88 regulations. The MCAI requires replacing the fuel LCU 1 and LCU 2; reworking the LCU 1 and LCU 2 supports; and segregating, replacing, and reworking some harnesses. 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 E:\FR\FM\30MYR1.SGM 30MYR1

Agencies

[Federal Register Volume 72, Number 103 (Wednesday, May 30, 2007)]
[Rules and Regulations]
[Pages 29874-29879]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10028]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-26857; Directorate Identifier 2006-NM-126-AD; 
Amendment 39-15069; AD 2007-11-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to all Airbus Model A310 series airplanes. That AD 
currently requires inspections of the lower door surrounding structure 
to detect cracks and corrosion; inspections to detect cracking of the 
holes of the corner doublers, the fail-safe ring, and the door frames 
of the door structures; and repair if necessary. That AD also currently

[[Page 29875]]

provides for optional terminating action for certain inspections. This 
new AD retains all requirements of the existing AD, mandates the 
previously optional terminating action, and reduces the applicability 
of the existing AD. This AD results from a determination that further 
rulemaking is necessary to improve the fatigue behavior of the cabin 
door surroundings. We are issuing this AD to prevent corrosion between 
the scuff plates at exit and cargo doors and fatigue cracks originating 
from certain fastener holes located in adjacent structure, which could 
result in reduced structural integrity of the door surroundings.

DATES: This AD becomes effective July 5, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 5, 2007.
    On September 4, 1998 (63 FR 40819, July 31, 1998), the Director of 
the Federal Register approved the incorporation by reference of certain 
other publications listed in the AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 98-16-06, amendment 39-
10682 (63 FR 40819, July 31, 1998). The existing AD applies to all 
Airbus Model A310 series airplanes. That NPRM was published in the 
Federal Register on January 19, 2007 (72 FR 2464). That NPRM proposed 
to retain the requirements of AD 98-16-06. These requirements are 
inspections of the lower door surrounding structure to detect cracks 
and corrosion; inspections to detect cracking of the holes of the 
corner doublers, the fail-safe ring, and the door frames of the door 
structures; and repair if necessary. That NPRM also proposed to mandate 
the previously optional terminating action, and reduce the 
applicability of the existing AD.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Give Credit for Previous Inspections

    FedEx concurs with the NPRM, but requests that we give credit for 
previous inspections (initial and repetitive) accomplished in 
accordance with AD 98-16-06. FedEx points out that this credit should 
be given for actions in paragraphs (f), (g), and (l) of the NPRM.
    We partially agree with the request. We agree that it is necessary 
for the AD to give credit for inspections accomplished previously in 
accordance with AD 98-16-06. We disagree that it is necessary to change 
the AD in this regard. Paragraph (e) of the AD states, ``You are 
responsible for having the actions required by this AD performed within 
the compliance times specified, unless the actions have already been 
done.'' Therefore, the AD already gives credit for required actions 
that were accomplished according to AD 98-16-06.

Explanation of New Service Information

    Airbus has issued Service Bulletin A310-53-2037, Revision 03, 
including Appendix 01, dated July 26, 2006. We referred in the NPRM to 
Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992; and 
Revision 02, dated November 27, 2000; as the appropriate source of 
service information for accomplishing certain actions. Revision 03 of 
the service bulletin updates the effectivity and improves the 
inspection and repair procedures. Revision 03 states that no additional 
work is required for airplanes modified in accordance with Revision 02 
or any previous revision. We have changed Table 1 in paragraph (n) of 
this AD to refer to Revision 03 for accomplishing certain required 
actions, and we have changed Table 3 in paragraph (p) of this AD to 
give credit to operators who accomplished the actions in accordance 
with Revision 02 of the service bulletin.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD. The average labor rate per work hour is $80.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Number of
                                                                       Cost per        U.S.-
            Action                Work hours           Parts           airplane      registered     Fleet cost
                                                                                     airplanes
----------------------------------------------------------------------------------------------------------------
Repetitive inspections behind  26..............  None............  $2,080.........           46  $95,680.
 scuff plates (required by AD
 98-16-06).
Repetitive inspections of      Between 4 and     None............  Between $320              46  Between
 corner doublers, fail-safe     100 depending                       and $8,000.                   $14,720, and
 ring, and door frames          on kit                                                            $368,000 per
 (required by AD 98-16-06).     purchased.                                                        inspection
                                                                                                  cycle.

[[Page 29876]]

 
Terminating modification for   Between 8 and 55  Between $506 and  Between $1,146            46  Between $52,716
 repetitive inspection of       depending on      $6,098            and $10,498.                  and $482,908.
 corner doublers, fail-safe     kit purchased.    depending on
 ring, and door frames.                           kit purchased.
----------------------------------------------------------------------------------------------------------------

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 have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10682 (63 FR 40819, July 31, 1998) and by adding 
the following new airworthiness directive (AD):

2007-11-12 Airbus: Amendment 39-15069. Docket No. FAA-2007-26857; 
Directorate Identifier 2006-NM-126-AD.

Effective Date

    (a) This AD becomes effective July 5, 2007.

Affected ADs

    (b) This AD supersedes AD 98-16-06.

Applicability

    (c) This AD applies to Airbus Model A310 series airplanes; 
certificated in any category; excluding those airplanes on which 
Airbus Modifications 5068, 7201, and 7298 have been incorporated in 
production.

Unsafe Condition

    (d) This AD results from a determination that further rulemaking 
is necessary to improve the fatigue behavior of the cabin door 
surroundings. We are issuing this AD to prevent corrosion between 
the scuff plates at exit and cargo doors and fatigue cracks 
originating from certain fastener holes located in adjacent 
structure, which could result in reduced structural integrity of the 
door surroundings.

Compliance

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

Requirements of AD 98-16-06

Initial Inspection Behind Scuff Plates and Repair if Necessary With 
Revised Affected Doors

    (f) Perform an initial inspection of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A310-53-2030, Revision 5, dated March 6, 1991, at the applicable 
time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If 
any crack or corrosion is found during this inspection, prior to 
further flight, repair in accordance with the service bulletin. 
Accomplishment of this inspection is not required for the aft 
passenger/crew doors if a steel doubler that covers the entire 
inspection area is installed.
    (1) For any door on which Modification 5382 and Modification 
5382D4741 for all other doors have been accomplished: Perform the 
initial inspection within 9 years since airplane manufacture, or 
within 1 year after September 4, 1998 (the effective date of AD 98-
16-06), whichever occurs later.
    (2) For any door on which Modification 5382 and Modification 
5382D4741 for all other doors have not been accomplished, and on 
which the procedures described in Airbus Service Bulletin A310-53-
2004, Revision 2, dated June 17, 1985; or Airbus Service Information 
Letter 53-033, Revision 2, dated November 23, 1984; have been 
accomplished: Perform the initial inspection within 5 years since 
airplane manufacture, or within 1 year after September 4, 1998, 
whichever occurs later.
    (3) For any door on which Modification 5382 and Modification 
5382D4741 for all other doors have not been accomplished, and on 
which the procedures described in Airbus Service Bulletin A310-53-
2004, Revision 2, dated June 17, 1985; or Airbus Service Information 
Letter 53-033, Revision 2, dated November 23, 1984; have not been 
accomplished: Perform the initial inspection within 4 years since 
airplane manufacture, or within 1 year after September 4, 1998, 
whichever occurs later.

Repetitive Inspections Behind Scuff Plates

    (g) Perform repetitive inspections of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A310-53-2041, Revision 02, dated July 2, 1996, at the applicable 
times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 
Accomplishment of these inspections is not required for the aft 
passenger/crew doors if

[[Page 29877]]

a steel doubler that covers the entire inspection area is installed.
    (1) For the forward passenger/crew doors, the bulk cargo door, 
and the aft passenger/crew doors, except the upper and lower edges 
of the fail-safe ring and the upper edges of the corner doubler, on 
all Model A310-200 and -300 series airplanes: Perform the first 
inspection within 5 years after accomplishing the inspection 
required by paragraph (f) of this AD; and repeat the inspection 
thereafter at intervals not to exceed 5 years.
    (2) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew door on 
all Model A310-200 series airplanes: Perform the first inspection 
within 5 years or 12,000 landings after accomplishing the inspection 
required by paragraph (f) of this AD, whichever occurs first; and 
repeat the inspection thereafter at intervals not to exceed 5 years 
or 12,000 landings, whichever occurs first.
    (3) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew door on 
all Model A310-300 series airplanes: Perform the first inspection 
within 5 years or 7,000 landings after accomplishing the inspection 
required by paragraph (f) of this AD, whichever occurs first; and 
repeat the inspection thereafter at intervals not to exceed 5 years 
or 7,000 landings, whichever occurs first.

Repair of Scuff Plates if Necessary

    (h) If any crack is found during any inspection required by 
paragraph (g) or (n) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A310-53-2041, Revision 02, 
dated July 2, 1996. Thereafter, perform the repetitive inspections 
required by paragraph (g) of this AD at the applicable times 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
    (i) If any corrosion is found during any inspection required by 
paragraph (g) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A310-53-2041, Revision 02, 
dated July 2, 1996. Thereafter, perform the repetitive inspections 
required by paragraph (g) of this AD at the applicable time 
specified in paragraph (i)(1) or (i)(2) of this AD.
    (1) For Model A310-200 series airplanes: Inspect at intervals 
not to exceed 5 years or 9,600 landings, whichever occurs first.
    (2) For Model A310-300 series airplanes: Inspect at intervals 
not to exceed 5 years or 5,600 landings, whichever occurs first.
    (j) Accomplishment of the actions required by paragraph (g), 
(h), or (i) of this AD in accordance with Airbus Service Bulletin 
A310-53-2041, dated December 5, 1990; or Revision 01, dated March 6, 
1991; prior to September 4, 1998, is acceptable for compliance with 
that paragraph.

Initial Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames

    (k) Perform an inspection to detect cracking of the holes of the 
corner doublers, the fail-safe ring, and the door frames of the 
left- and right-hand forward, mid, and aft passenger/crew door 
structures, in accordance with Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992, and at the applicable times 
specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
    (1) For the upper corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 2,000 landings 
after September 4, 1998, whichever occurs later.
    (2) For the lower corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 4,000 landings 
after September 4, 1998, whichever occurs later.
    (3) For the upper and lower corners of the aft doors, and for 
the parts underneath the corners of the upper door frames: Inspect 
prior to the accumulation of 20,000 total landings, or within 4,000 
landings after September 4, 1998, whichever occurs later.

Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door 
Frames

    (l) Repeat the inspections required by paragraph (k) of this AD 
at the applicable times specified in paragraphs (l)(1), (l)(2), 
(l)(3), (l)(4), and (l)(5).
    (1) For the upper corners of the forward doors: Inspect at 
intervals not to exceed 6,000 landings.
    (2) For the lower corners of the forward doors: Inspect at 
intervals not to exceed 10,000 landings.
    (3) For the upper and lower corners of the aft doors on which an 
inspection required by paragraph (k) of this AD was accomplished 
using a ROTO test technique: Inspect at intervals not to exceed 
8,000 landings.
    (4) For the upper and lower corners of the aft doors on which an 
inspection required by paragraph (k) of this AD was accomplished 
using an x-ray technique: Inspect at intervals not to exceed 3,500 
landings.
    (5) For the areas around the fasteners in the vicinity of 
stringer 12 on the upper door frames of the aft doors on which an 
inspection required by paragraph (k) of this AD was accomplished 
using a visual technique: Inspect at intervals not to exceed 6,900 
landings.

Repair of Corner Doublers, Fail-Safe Ring, and/or Door Frames if 
Necessary

    (m) If any crack is found during any inspection required by 
paragraph (k) or (l) of this AD: Prior to further flight, accomplish 
the requirement of paragraph (m)(1) or (m)(2) of this AD, as 
applicable.
    (1) If any crack is found, and the crack can be eliminated using 
the method specified in Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 
2000: Prior to further flight, repair the crack in accordance with 
that service bulletin.
    (2) If any crack is found, and the crack cannot be eliminated 
using the method specified in Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 
2000: Prior to further flight, repair the crack in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.

New Requirements of This AD

New Revision of Service Bulletins

    (n) As of the effective date of this AD, use only the service 
bulletins specified in Table 1 of this AD.

               Table 1.--New Revision of Service Bulletins
------------------------------------------------------------------------
                                              In accordance with the
     Do the action(s) required by--       accomplishment instructions of
                                            Airbus Service Bulletin--
------------------------------------------------------------------------
(1) Paragraph (f) of this AD...........  A310-53-2030, Revision 06,
                                          dated July 2, 1996.
(2) Paragraph (k) and (m)(1) of this AD  A310-53-2037, Revision 03,
                                          excluding Appendix 01, dated
                                          July 26, 2006.
------------------------------------------------------------------------

Terminating Modification for Repetitive Inspection of Corner Doublers, 
Fail-Safe Ring, and Door Frames

    (o) Modify the passenger/crew door structures in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A310-53-
2017, Revision 09, dated May 17, 2004. Do the modification at the 
applicable time in paragraph (o)(1) or (o)(2) of Table 2 of this AD. 
Accomplishment of this modification constitutes terminating action 
for the repetitive inspections required by paragraph (l) of this AD. 
The inspections required by paragraph (f) of this AD must be done 
before accomplishing this modification.

[[Page 29878]]



         Table 2.--Compliance Time for Terminating Modification
------------------------------------------------------------------------
              For model--                        Compliance time
------------------------------------------------------------------------
(1) A310-203, -204, -221, and -222       Before the accumulation of
 airplanes.                               40,000 flight cycles since the
                                          date of issuance of the
                                          original French standard
                                          Airworthiness Certificate or
                                          the date of issuance of the
                                          original French Export
                                          Certificate of Airworthiness,
                                          or during the next inspection
                                          required by paragraph (l) of
                                          this AD, whichever occurs
                                          later.
(2) A310-304, -322, -324, and -325       Before the accumulation of
 airplanes.                               35,000 flight cycles since the
                                          date of issuance of the
                                          original French standard
                                          Airworthiness Certificate or
                                          the date of issuance of the
                                          original French Export
                                          Certificate of Airworthiness,
                                          or during the next inspection
                                          required by paragraph (l) of
                                          this AD, whichever occurs
                                          later.
------------------------------------------------------------------------

Earlier Revision of Service Bulletins

    (p) Actions done before the effective date of this AD in 
accordance with the service bulletins identified in Table 3 of this 
AD are acceptable for compliance with the corresponding requirements 
of this AD.

           Table 3.--Earlier Revision(s) of Service Bulletins
------------------------------------------------------------------------
                                  Revision
    Airbus Service Bulletin        level                 Date
------------------------------------------------------------------------
(1) A310-53-2017..............           07  February 25, 1992.
(2) A310-53-2017..............           08  September 7, 2000.
(3) A310-53-2037..............           02  November 27, 2000.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (q)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 98-16-06 are approved as alternative methods of 
compliance with the corresponding provisions of paragraphs (f) 
through (m) of this AD.
    (3) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (r) French airworthiness directives 1991-132-124(B) R1, dated 
November 29, 2000, and F-2004-103, dated July 7, 2004, also address 
the subject of this AD.

Material Incorporated by Reference

    (s) You must use the service information listed in Table 4 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

            Table 4.--All Material Incorporated by Reference
------------------------------------------------------------------------
                                  Revision
    Airbus Service Bulletin        level                 Date
------------------------------------------------------------------------
A310-53-2017..................           09  May 17, 2004.
A310-53-2030..................            5  March 6, 1991.
A310-53-2030..................           06  July 2, 1996.
A310-53-2037..................            1  April 29, 1992.
A310-53-2037, excluding                  02  November 27, 2000.
 Appendix 01.
A310-53-2037, excluding                  03  July 26, 2006.
 Appendix 01.
A310-53-2041..................           02  July 2, 1996.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the documents listed in Table 5 of 
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

            Table 5.--New Material Incorporated by Reference
------------------------------------------------------------------------
                                  Revision
    Airbus Service Bulletin        level                 Date
------------------------------------------------------------------------
A310-53-2017..................           09  May 17, 2004.
A310-53-2030..................           06  July 2, 1996.
A310-53-2037..................            1  April 29, 1992.
A310-53-2037, excluding                  02  November 27, 2000.
 Appendix 01.
A310-53-2037, excluding                  03  July 26, 2006.
 Appendix 01.
------------------------------------------------------------------------


[[Page 29879]]

    Airbus Service Bulletin A310-53-2037, Revision 1, dated April 
29, 1992, contains the following effective pages:

----------------------------------------------------------------------------------------------------------------
                 Page No.                  Revision level shown on page             Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 4, 6, 11-15, 18, 29, 39-44, 46, 57....  Revision 1..................  April 29, 1992.
2, 3, 5, 7-10, 16, 17, 19-28, 30-38,       Original....................  December 11, 1990.
 45,47-56, 58-60.
----------------------------------------------------------------------------------------------------------------

    (2) On September 4, 1998 (63 FR 40819, July 31, 1998), the 
Director of the Federal Register approved the incorporation by 
reference of the service information listed in Table 6 of this AD.

         Table 6.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
                                     Revision
     Airbus Service Bulletin          level               Date
------------------------------------------------------------------------
A310-53-2030.....................            5  March 6, 1991.
A310-53-2041.....................           02  July 2, 1996.
------------------------------------------------------------------------

    (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; 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: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-10028 Filed 5-29-07; 8:45 am]
BILLING CODE 4910-13-P