Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 33994-34000 [06-5244]

Download as PDF 33994 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations Restatement of Requirements of AD 99–12– 08 One-Time External Detailed Inspection (f) Prior to the accumulation of 29,000 total flight cycles or within 250 flight cycles after August 9, 1993 (the effective date AD 93–13– 02, amendment 39–8615, which was superseded by AD 99–12–08), whichever occurs later, accomplish an external detailed inspection to detect cracks of the fuselage skin between stringers 19 left and 25 left and at BS 360 to BS 540, in accordance with Boeing Alert Service Bulletin 737–53A1160, dated October 24, 1991; or Boeing Service Bulletin 737–53A1160, Revision 1, dated April 29, 1993. If any crack is found, prior to further flight, accomplish the requirements of paragraphs (f)(1) and (f)(2) of this AD. (1) Perform an internal detailed inspection to detect cracks of the frames between stringers 19 left and 25 left and at BS 360 to BS 500B, in accordance with either service bulletin. (2) Repair all cracks in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), Transport Airplane Directorate, FAA. mstockstill on PROD1PC61 with RULES Internal Detailed Inspections (g) Within 3,000 flight cycles after completing the requirements of paragraph (f) of this AD, unless accomplished within the last 6,000 flight cycles prior to August 9, 1993, perform an internal detailed inspection to detect cracks of the frames between stringers 19 left and 25 left and at body stations 360 to 500B, in accordance with Boeing Alert Service Bulletin 737–53A1160, dated October 24, 1991; or Boeing Service Bulletin 737–53A1160, Revision 1, dated April 29, 1993. Thereafter, repeat the internal detailed inspection at intervals not to exceed 9,000 flight cycles. If any crack is found during any inspection required by this paragraph, before further flight, repair as specified in paragraph (g)(1) or (g)(2) of this AD, as applicable. (1) If any crack is found that does not exceed the limits specified in the Boeing 737 Structural Repair Manual (SRM), repair the crack in accordance with a method approved by the Manager, Seattle ACO; or in accordance with the procedures specified in paragraph (k)(4) of this AD. The SRM is one approved source of information for accomplishing the requirements of this paragraph. Repeat the internal detailed inspection thereafter at intervals not to exceed 9,000 flight cycles. (2) If any crack is found that exceeds the limits specified in the SRM, repair the crack in accordance with a method approved by the Manager, Seattle ACO; or in accordance with the procedures specified in paragraph (k)(4) of this AD. Repeat the internal detailed visual inspection thereafter at intervals not to exceed 9,000 flight cycles. Install Doublers (h) Prior to the accumulation of 75,000 total flight cycles, or within 3,000 flight cycles after July 16, 1999 (the effective date of AD 99–12–08), whichever occurs later, install doublers on the specified frames located between stringers 19 left and 25 left from BS 360 to BS 500B, in accordance with VerDate Aug<31>2005 14:46 Jun 12, 2006 Jkt 208001 Boeing Service Bulletin 737–53A1160, Revision 1, dated April 29, 1993. Installing these doublers on the specified fuselage frames ends the repetitive inspections required by paragraphs (f) and (g) of this AD. New Requirements of This AD Repetitive Inspection of Certain Frames (i) Within 9,000 flight cycles after accomplishing the modification required by paragraph (h) of this AD, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later, perform an internal detailed inspection to detect cracking in the fuselage frame at BS 360 and the fuselage frame at BS 500, between stringers 19 left and 25 left, in accordance with Boeing Alert Service Bulletin 737– 53A1160, dated October 24, 1991; or Boeing Service Bulletin 737–53A1160, Revision 1, dated April 29, 1993. Thereafter, repeat the internal detailed inspection of the BS 360 and BS 500 frames at intervals not to exceed 9,000 flight cycles. (j) If any crack is found during any inspection required by paragraph (i) of this AD, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously in accordance with AD 99–12–08, including AMOCs approved previously in accordance with AD 93–13–02, are approved as AMOCs for the corresponding provisions specified in paragraphs (f), (g), and (h) of this AD. (4) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Material Incorporated by Reference (l) You must use Boeing Alert Service Bulletin 737–53A1160, dated October 24, 1991; or Boeing Service Bulletin 737– PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 53A1160, Revision 1, dated April 29, 1993, as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents on August 9, 1993 (58 FR 36863, July 9, 1993). Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 5, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5287 Filed 6–12–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19002; Directorate Identifier 2003–NM–27–AD; Amendment 39– 14639; AD 2006–12–13] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4–600, B4–600R, and F4–600R Series Airplanes; and Model C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 and A300–600 series airplanes. That AD currently requires repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. That AD also requires modification of Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. This new AD requires new repetitive inspections at reduced compliance times. This new AD also requires new repetitive inspections of certain areas of the E:\FR\FM\13JNR1.SGM 13JNR1 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations mstockstill on PROD1PC61 with RULES attachment fittings that were repaired in accordance with the actions specified in the existing AD. This AD results from new service information that was issued by the manufacturer and mandated by the French airworthiness authority. We are issuing this AD to prevent fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective July 18, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 18, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications, as listed in the AD, on April 12, 2000 (65 FR 12077, March 8, 2000). The Director of the Federal Register approved the incorporation by reference of certain other publications, as listed in the AD, on October 20, 1999 (64 FR 49966, September 15, 1999). 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. For Model A300 B2 and A300 B4 series airplanes, contact Jacques Leborgne, Airbus Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, fax (+33) 5 61 93 36 14, for service information identified in this AD. For Model A300–600 series airplanes, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the 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. VerDate Aug<31>2005 14:46 Jun 12, 2006 Jkt 208001 Discussion The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2000–05–07, amendment 39–11616 (65 FR 12077, March 8, 2000), and applies to certain Airbus Model A300 B2 and A300 B4 series airplanes; and Model A300–600 series airplanes. That supplemental NPRM was published in the Federal Register on March 27, 2006 (71 FR 15068). That supplemental NPRM proposed to reduce the compliance times for all inspections required by AD 2000–05–07; to require inspections in accordance with new revisions of the service bulletins; and to require new repetitive inspections of certain areas of the attachment fittings that were repaired in accordance with the actions specified in the existing AD. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Give Credit for Previous Revisions of Certain Service Bulletins Airbus states that Service Bulletins A300–57–6088, Revision 03, dated March 13, 2003; and A300–57–0235, Revision 02, dated September 27, 1999; are not referenced in Table 3 of the supplemental NPRM for the terminating modification. Airbus notes that these service bulletins are listed in the document index of Docket No. FAA– 2004–19002. Airbus reviewed the technical content of these two service bulletins and states that there is no technical reason why they should not be acceptable for complying with the actions proposed in the supplemental NPRM. Airbus therefore requests that we include these service bulletins in Table 3 of the final rule. We partially agree. We agree that both service bulletins are acceptable for compliance with the corresponding actions proposed in the supplemental NPRM. We do not agree with adding these service bulletins to Table 3 of the final rule. Table 3 refers only to service bulletins that were required by either AD 2000–05–07 or the AD that it superseded, which was AD 99–19–26, amendment 39–11313 (64 FR 49966, September 15, 1999); or that are the latest revisions proposed for the supplemental NPRM. Table 6 of the supplemental NPRM refers to issues of service bulletins that are not the latest PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 33995 revisions, and were not required by the superseded ADs, but are still acceptable for compliance. Both Airbus Service Bulletin A300–57–6088, Revision 03, and A300–57–0235, Revision 02, are listed in Table 6 of the final rule. We have not changed the final rule in this regard. Explanation of Editorial Changes to the Final Rule We inadvertently removed words from the following paragraph of the supplemental NPRM: ‘‘§ 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD).’’ We have changed this paragraph in the final rule to include words that remove the original NPRM as follows: ‘‘§ 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–11616 (65 FR 12077, March 8, 2000), and adding the following new airworthiness directive (AD).’’ We have revised paragraph (i)(1) of the final rule to identify model designations as published in the most recent type certificate data sheet for the affected models. Paragraphs (g)(2), (j)(2), (l), and (m) of the supplemental NPRM specify making repairs using a method approved by ´ ´ either the FAA or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). The European Aviation Safety Agency (EASA) has assumed responsibility for the airplane models subject to this AD. Therefore, we have revised paragraphs (g)(2), (j)(2), (l), and (m) of the final rule to specify making repairs using a method approved by either the FAA or the EASA (or its delegated agent). Conclusion We have carefully reviewed the available data, including the comment 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. E:\FR\FM\13JNR1.SGM 13JNR1 33996 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations ESTIMATED COSTS Action Average labor rate per hour Work hours Modification (required by AD 2000–05– 07) ........................................................ Pre-modification inspections (new action), per inspection cycle .................... Post-modification inspections (new action), per inspection cycle .................... Cost per airplane Parts Number of U.S.-cost registered airplanes Fleet cost 70 $65 $10,270 $14,820 164 $2,430,480 6 65 (1) 2 390 164 2 63,960 2 65 (1) 2 130 164 221,320 1 None. 2 Per inspection cycle. 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 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 39–11616 (65 FR 12077, March 8, 2000), and adding the following new airworthiness directive (AD): I 2006–12–13 Airbus: Amendment 39–14639. Docket No. FAA–2004–19002; Directorate Identifier 2003–NM–27–AD. Effective Date (a) This AD becomes effective July 18, 2006. Affected ADs (b) This AD supersedes AD 2000–05–07, amendment 39–11616. Applicability (c) This AD applies to Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4– 103, and B4–203 airplanes, as identified in Airbus Service Bulletin A300–57A0234, Revision 05, dated February 19, 2002; and Model A300 B4–601, B4–603, B4–620, B4– 622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes, as identified in Airbus Service Bulletin A300– 57A6087, Revision 04, dated February 19, 2002; except airplanes on which Airbus Modification 11912 or 11932 has been installed; certificated in any category. Unsafe Condition (d) This AD was prompted by new service information that was issued by the manufacturer and mandated by the French airworthiness authority. We are issuing this AD to prevent fatigue cracking of the main landing gear (MLG) attachment fittings, which could result in reduced structural integrity of the airplane. 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. Restatement of the Requirements of AD 2000–05–07 Repetitive Inspections (f) Perform a detailed inspection and a high-frequency eddy current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG attachment fittings at the lower flange, in accordance with the Accomplishment Instructions of any applicable service bulletin listed in Table 1 and Table 2 of this AD, at the time specified in paragraph (f)(1) or (f)(2) of this AD. After April 12, 2000 (the effective date of AD 2000–05–07), only the service bulletins listed in Table 2 of this AD may be used. Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles, until paragraph (h), (i), or (k) of this AD is accomplished. mstockstill on PROD1PC61 with RULES TABLE 1.—REVISION 01 OF SERVICE BULLETINS Model Airbus Service Bulletin A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and A300 C4–605R Variant F airplanes. A300–57–6087 VerDate Aug<31>2005 14:46 Jun 12, 2006 Jkt 208001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\13JNR1.SGM Revision level 01 13JNR1 Date March 11, 1998. 33997 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations TABLE 1.—REVISION 01 OF SERVICE BULLETINS—Continued Model Airbus Service Bulletin A300 B2 and A300 B4 series airplanes ........................................................................ A300–57–0234 Revision level 01 Date March 11, 1998. TABLE 2.—FURTHER REVISIONS OF SERVICE BULLETINS Model Airbus Service Bulletin A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, FA–605R, F4–622R, and A300 C4–605R Variant F airplanes. A300–57A6087 *02 June 24, 1999. A300–57A0234 *03 *04 02 *03 *04 *05 May 19, 2000. February 19, 2002. June 24, 1999. September 2, 1999. May 19, 2000. February 19, 2002. A300 B2 and A300 B4 series airplanes ........................................................................ Revision level Date * Including Appendix 01. (1) For airplanes that have accumulated 20,000 or more total flight cycles as of March 9, 1998 (the effective date of AD 98–03–06, amendment 39–10298): Inspect within 500 flight cycles after March 9, 1998. (2) For airplanes that have accumulated less than 20,000 total flight cycles as of March 9, 1998: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after March 9, 1998, whichever occurs later. Note 1: For the purposes of this AD, a detailed inspection is defined as: ‘‘An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.’’ Note 2: Accomplishment of the initial detailed and HFEC inspections in accordance with Airbus Service Bulletin A300–57A0234 or A300–57A6087, both dated August 5, 1997, as applicable, is considered acceptable for compliance with the initial inspections required by paragraph (f) of this AD. Repair (g) If any crack is detected during any inspection required by paragraph (f) of this AD, prior to further flight, accomplish the requirements of paragraph (g)(1) or (g)(2) of this AD, as applicable. (1) If a crack is detected at one hole only, and the crack does not extend out of the spotface of the hole, repair in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD. (2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent). Terminating Modification (h) Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999 (the effective date of AD 99–19–26, amendment 39–11313), whichever occurs later: Modify Gear Rib 5 of the MLG attachment fittings at the lower flange in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 3 of this AD. After the effective date of this AD, only Revision 04 of Airbus Service Bulletin A300–57–6088, and Revisions 04 and 05 of Airbus Service Bulletin A300–57–0235 may be used. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of paragraphs (f) and (i) of this AD. TABLE 3.—SERVICE BULLETINS FOR TERMINATING MODIFICATION Model Airbus Service Bulletin A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, A300 C4–605R Variant F airplanes. A300–57–6088 A300 B2 and A300 B4 series airplanes ........................................................................ Revision level Date * 01 02 04 * 01 03 04 05 A300–57–0235 February 1, 1999. September 5, 2002. December 3, 2003. February 1, 1999. September 5, 2002. March 13, 2003. December 3, 2003. mstockstill on PROD1PC61 with RULES * Including Appendix 01. Note 3: Accomplishment of the modification required by paragraph (h) of this AD prior to April 12, 2000, in accordance with Airbus Service Bulletin A300–57–6088 or A300–57–0235, both dated August 5, 1998; as applicable; is acceptable for compliance with the requirements of that paragraph. VerDate Aug<31>2005 14:46 Jun 12, 2006 Jkt 208001 New Requirements of This AD New Repetitive Inspections (i) For airplanes on which the modification specified in paragraph (h) or (k) of this AD has not been done as of the effective date of this AD, perform a detailed and an HFEC inspection to detect cracks of the lower flange of Gear Rib 5 of the MLG at holes 43, 47, 48, 49, 50, 52, and 54, in accordance with PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 the applicable service bulletin listed in Table 4 of this AD. Perform the inspections at the applicable time specified in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD. Repeat the inspections thereafter at intervals not to exceed 700 flight cycles until the terminating modification required by paragraph (k) of this AD is accomplished. Accomplishment of the inspections per paragraph (i) of this AD, E:\FR\FM\13JNR1.SGM 13JNR1 33998 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations terminates the inspection requirements of paragraph (f) of this AD. TABLE 4.—SERVICE BULLETINS FOR REPETITIVE INSPECTIONS Model Airbus Service Bulletin A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes. A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes ...... A300–57A6087 * 04 February 19, 2002. A300–57A0234 * 05 February 19, 2002. Revision level Date * Including Appendix 01. (1) For Model A300 B2–1A, B2–1C, B2K– 3C, B2–203, B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes; and Model C4–605R Variant F airplanes that have accumulated 18,000 or more total flight cycles as of the effective date of this AD: Within 700 flight cycles after the effective date of this AD. (2) For Model A300 B2–1A, B2–1C, B2K– 3C, and B2–203 airplanes that have accumulated less than 18,000 total flight cycles as of the effective date of this AD: Prior to the accumulation of 18,000 total flight cycles, or within 700 flight cycles after the effective date of this AD, whichever occurs later. (3) For Model A300 B4–2C, B4–103, and B4–203 airplanes that have accumulated less than 18,000 total flight cycles as of the effective date of this AD: Prior to the accumulation of 14,500 total flight cycles, or within 700 flight cycles after the effective date of this AD, whichever occurs later. (4) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes that have accumulated less than 18,000 total flight cycles as of the effective date of this AD: Prior to the accumulation of 11,600 total flight cycles, or within 700 flight cycles after the effective date of this AD, whichever occurs later. (2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM–116, or the EASA (or its delegated agent). Crack Repair (j) If any crack is detected during any inspection required by paragraph (i) of this AD, prior to further flight, accomplish the requirements of paragraph (j)(1) and (j)(2) of this AD, as applicable. (1) If a crack is detected at only one hole, and the crack does not extend out of the spotface of the hole, repair in accordance with Airbus Service Bulletin A300–57A0234, Revision 05, including Appendix 01, dated February 19, 2002 (for Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes); or A300–57A6087, Revision 04, including Appendix 01, dated February 19, 2002 (for Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, F4–605R, F4–622R, and C4–605R airplanes); as applicable. (k) For airplanes on which the terminating modification in paragraph (h) of this AD has not been accomplished before the effective date of this AD: At the earlier of the times specified in paragraphs (k)(1) and (k)(2) of this AD, modify Gear Rib 5 of the MLG attachment fittings at the lower flange. Except as provided by paragraph letter (l) of this AD, do the modification in accordance with the applicable service bulletin in Table 5 of this AD. This action terminates the repetitive inspections requirements of paragraphs (f) and (i) of this AD. (1) Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999, whichever is later. (2) Within 16 months after the effective date of this AD. Terminating Modification TABLE 5.—SERVICE BULLETINS FOR TERMINATING MODIFICATION Model Airbus Service Bulletin A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes. A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 05 2003 airplanes. A300–57–6088 04 December 3, 2003. A300–57–0235 04 05 March 13, 2003. December 3, 2003. mstockstill on PROD1PC61 with RULES (l) Where the applicable service bulletin in paragraph (k) of this AD specifies to contact Airbus for modification instructions; or if there is a previously installed repair at any of the affected fastener holes; or if a crack is found when accomplishing the modification: Prior to further flight, modify in accordance with a method approved by the Manager, International Branch, ANM–116, or the EASA (or its delegated agent). Post-Modification Inspections (m) Within 700 flight cycles after doing the modification in accordance with paragraph (h), (k), or (l) of this AD, or within 6 months after the effective date of this AD, whichever occurs later, except as provided by paragraph (o) of this AD: Do a detailed and an HFEC inspection for cracks at holes 47 and 54 in VerDate Aug<31>2005 14:46 Jun 12, 2006 Jkt 208001 the lower flange of Gear Rib 5, and do all related investigative and corrective actions before further flight, by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A300– 57A0246, including Appendix 01, dated May 20, 2005; or Airbus Service Bulletin A300– 57A6101, including Appendix 01, dated May 20, 2005; as applicable. Where the applicable service bulletin specifies to contact Airbus for repair instructions: Prior to further flight, modify in accordance with a method approved by the Manager, International Branch, ANM–116, or the EASA (or its delegated agent). Repeat the inspection and related investigative and corrective actions thereafter at intervals not to exceed 700 flight cycles. If no crack is detected during the PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Revision level Date repeat inspection performed at or above 2,100 flight cycles after doing the modification in accordance with paragraph (h), (k), or (l) of this AD, then no further inspection is required. Except, at least one inspection is required after the accumulation of 2,100 flight cycles after installing the modification in accordance with paragraph (h) or (k) of this AD. Actions Accomplished Per Previous Issues of the Service Bulletins (n) Actions accomplished before the effective date of this AD, per the service bulletins listed in Table 6 of this AD, are considered acceptable for compliance with the corresponding action specified in this AD. E:\FR\FM\13JNR1.SGM 13JNR1 33999 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations TABLE 6.—PREVIOUS ISSUES OF SERVICE BULLETINS Airbus Service Bulletin Revision level A300–57–0235 ............................................................................................................................................. * 02 A300–57–6088 ............................................................................................................................................. 03 02 03 Date September 27, 1999. September 5, 2002. September 5, 2000. March 13, 2003. * Including Appendix 01. Reporting (o)(1) Although Airbus Service Bulletins A300–57A0234, A300–57–0235, A300– 57A6087, A300–57–6088, A300–57A0246, and A300–57A6101, specify to submit certain information to the manufacturer, this AD does not include such a requirement, except as provided by paragraph (o)(2) of this AD. (2) Where Airbus Service Bulletins A300– 57A0246 and A300–57A6101 specify to submit a report of positive and negative findings of the post-modification inspection required by paragraph (m) of this AD, within 30 days after the effective date of this AD, submit a report only of the positive findings of post-modification inspections to Airbus, Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) 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. (3) AMOCs approved previously per AD 2000–05–07 are approved as AMOCs with this AD. Related Information (q) French airworthiness directives 2003– 318(B), dated August 20, 2003; and F–2005– 113 R1, dated July 20, 2005; also address the subject of this AD. Material Incorporated by Reference (r) You must use the service information listed in Table 7 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 7.—MATERIAL INCORPORATED BY REFERENCE Revision level Airbus Service Bulletin A300–57A0234 A300–57A0234 A300–57A0234 A300–57A0234 A300–57A0246 A300–57A6087 A300–57A6087 A300–57A6087 A300–57A6101 A300–57–0234 A300–57–0235 A300–57–0235 A300–57–0235 A300–57–0235 A300–57–6087 A300–57–6088 A300–57–6088 A300–57–6088 ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... 02 ............... * 03 .............. * 04 .............. * 05 .............. Original * ...... * 02 .............. * 03 .............. * 04 .............. Original * ...... 01 ............... * 01 .............. 03 ............... 04 ............... 05 ............... 01 ............... * 01 .............. 02 ............... 04 ............... Date June 24, 1999. September 2, 1999. May 19, 2000. February 19, 2002. May 20, 2005. June 24, 1999. May 19, 2000. February 19, 2002. May 20, 2005. March 11, 1998. February 1, 1999. September 5, 2002. March 13, 2003. December 3, 2003. March 11, 1998. February 1, 1999. September 5, 2002. December 3, 2003. * Including Appendix 01. (1) The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 8 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 8.—NEW MATERIAL INCORPORATED BY REFERENCE Revision level mstockstill on PROD1PC61 with RULES Airbus Service Bulletin A300–57A0234 A300–57A0234 A300–57A0246 A300–57A6087 A300–57A6087 A300–57A6101 A300–57–0235 A300–57–0235 VerDate Aug<31>2005 ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... 15:19 Jun 12, 2006 Jkt 208001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\13JNR1.SGM * 04 .............. * 05 .............. Original * ...... * 03 .............. * 04 .............. Original * ...... 03 ............... 04 ............... 13JNR1 Date May 19, 2000. February 19, 2002. May 20, 2005. May 19, 2000. February 19, 2002. May 20, 2005. September 5, 2002. March 13, 2003. 34000 Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations TABLE 8.—NEW MATERIAL INCORPORATED BY REFERENCE—Continued Airbus Service Bulletin Revision level A300–57–0235 ............................................................................................................................................... A300–57–6088 ............................................................................................................................................... A300–57–6088 ............................................................................................................................................... 05 ............... 02 ............... 04 ............... Date December 3, 2003. September 5, 2002. December 3, 2003. * Including Appendix 01. (2) On April 12, 2000 (65 FR 12077, March 8, 2000), the Director of the Federal Register approved the incorporation by reference of the documents listed in Table 9 of this AD. TABLE 9.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Airbus Service Bulletin Revision level A300–57A0234 ............................................................................................................................................ A300–57A0234 ............................................................................................................................................ A300–57A6087 ............................................................................................................................................ 02 * 03 * 02 Date June 24, 1999. September 2, 1999. June 24, 1999. * Including Appendix 01. (3) On October 20, 1999 (64 FR 49966, September 15, 1999), the Director of the Federal Register approved the incorporation by reference of the documents listed in Table 10 of this AD. TABLE 10.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Airbus Service Bulletin A300–57–0234 A300–57–0235 A300–57–6087 A300–57–6088 Revision level ............................................................................................................................................. ............................................................................................................................................. ............................................................................................................................................. ............................................................................................................................................. 01 * 01 01 * 01 Date March 11, 1998. February 1, 1999. March 11, 1998. February 1, 1999. * Including Appendix 01. (4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 31, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5244 Filed 6–12–06; 8:45 am] mstockstill on PROD1PC61 with RULES 14:46 Jun 12, 2006 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24076; Directorate Identifier 2006–NM–015–AD; Amendment 39–14640; AD 2006–12–14] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira del Aeronautica S.A. (EMBRAER) Model EMB–120, –120ER, –120FC, –120QC, and –120RT Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB–120, –120ER, –120FC, –120QC, and –120RT airplanes. This AD requires replacing the shut-off and crossbleed valves of the bleed air system with new valves having hermetically sealed switches. This AD results from fuel system reviews conducted by the manufacturer. We are BILLING CODE 4910–13–P VerDate Aug<31>2005 DEPARTMENT OF TRANSPORTATION Jkt 208001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 issuing this AD to prevent a potential source of ignition near a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: This AD becomes effective July 18, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 18, 2006. 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this AD. 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\13JNR1.SGM 13JNR1

Agencies

[Federal Register Volume 71, Number 113 (Tuesday, June 13, 2006)]
[Rules and Regulations]
[Pages 33994-34000]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5244]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-27-AD; 
Amendment 39-14639; AD 2006-12-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series 
Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and 
Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series 
Airplanes)

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A300 and A300-600 series 
airplanes. That AD currently requires repetitive inspections to detect 
cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings 
at the lower flange, and repair, if necessary. That AD also requires 
modification of Gear Rib 5 of the MLG attachment fittings, which 
constitutes terminating action for the repetitive inspections. This new 
AD requires new repetitive inspections at reduced compliance times. 
This new AD also requires new repetitive inspections of certain areas 
of the

[[Page 33995]]

attachment fittings that were repaired in accordance with the actions 
specified in the existing AD. This AD results from new service 
information that was issued by the manufacturer and mandated by the 
French airworthiness authority. We are issuing this AD to prevent 
fatigue cracking of the MLG attachment fittings, which could result in 
reduced structural integrity of the airplane.

DATES: This AD becomes effective July 18, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 18, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications, as listed in the AD, on April 12, 
2000 (65 FR 12077, March 8, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications, as listed in the AD, on 
October 20, 1999 (64 FR 49966, September 15, 1999).

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.
    For Model A300 B2 and A300 B4 series airplanes, contact Jacques 
Leborgne, Airbus Customer Service Directorate, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France, fax (+33) 5 61 93 36 14, for 
service information identified in this AD. For Model A300-600 series 
airplanes, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the 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 supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that supersedes AD 2000-05-07, 
amendment 39-11616 (65 FR 12077, March 8, 2000), and applies to certain 
Airbus Model A300 B2 and A300 B4 series airplanes; and Model A300-600 
series airplanes. That supplemental NPRM was published in the Federal 
Register on March 27, 2006 (71 FR 15068). That supplemental NPRM 
proposed to reduce the compliance times for all inspections required by 
AD 2000-05-07; to require inspections in accordance with new revisions 
of the service bulletins; and to require new repetitive inspections of 
certain areas of the attachment fittings that were repaired in 
accordance with the actions specified in the existing AD.

Comments

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

Request To Give Credit for Previous Revisions of Certain Service 
Bulletins

    Airbus states that Service Bulletins A300-57-6088, Revision 03, 
dated March 13, 2003; and A300-57-0235, Revision 02, dated September 
27, 1999; are not referenced in Table 3 of the supplemental NPRM for 
the terminating modification. Airbus notes that these service bulletins 
are listed in the document index of Docket No. FAA-2004-19002. Airbus 
reviewed the technical content of these two service bulletins and 
states that there is no technical reason why they should not be 
acceptable for complying with the actions proposed in the supplemental 
NPRM. Airbus therefore requests that we include these service bulletins 
in Table 3 of the final rule.
    We partially agree. We agree that both service bulletins are 
acceptable for compliance with the corresponding actions proposed in 
the supplemental NPRM. We do not agree with adding these service 
bulletins to Table 3 of the final rule. Table 3 refers only to service 
bulletins that were required by either AD 2000-05-07 or the AD that it 
superseded, which was AD 99-19-26, amendment 39-11313 (64 FR 49966, 
September 15, 1999); or that are the latest revisions proposed for the 
supplemental NPRM. Table 6 of the supplemental NPRM refers to issues of 
service bulletins that are not the latest revisions, and were not 
required by the superseded ADs, but are still acceptable for 
compliance. Both Airbus Service Bulletin A300-57-6088, Revision 03, and 
A300-57-0235, Revision 02, are listed in Table 6 of the final rule. We 
have not changed the final rule in this regard.

Explanation of Editorial Changes to the Final Rule

    We inadvertently removed words from the following paragraph of the 
supplemental NPRM: ``Sec.  39.13 [Amended] 2. The Federal Aviation 
Administration (FAA) amends Sec.  39.13 by adding the following new 
airworthiness directive (AD).'' We have changed this paragraph in the 
final rule to include words that remove the original NPRM as follows: 
``Sec.  39.13 [Amended] 2. The Federal Aviation Administration (FAA) 
amends Sec.  39.13 by removing amendment 39-11616 (65 FR 12077, March 
8, 2000), and adding the following new airworthiness directive (AD).''
    We have revised paragraph (i)(1) of the final rule to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.
    Paragraphs (g)(2), (j)(2), (l), and (m) of the supplemental NPRM 
specify making repairs using a method approved by either the FAA or the 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its 
delegated agent). The European Aviation Safety Agency (EASA) has 
assumed responsibility for the airplane models subject to this AD. 
Therefore, we have revised paragraphs (g)(2), (j)(2), (l), and (m) of 
the final rule to specify making repairs using a method approved by 
either the FAA or the EASA (or its delegated agent).

Conclusion

    We have carefully reviewed the available data, including the 
comment 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.

[[Page 33996]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                                                                           Average labor                     Cost per          cost
                         Action                             Work hours     rate per hour       Parts         airplane       registered      Fleet cost
                                                                                                                             airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification (required by AD 2000-05-07)................              70             $65         $10,270         $14,820             164      $2,430,480
Pre-modification inspections (new action), per                         6              65             (1)           2 390             164        2 63,960
 inspection cycle.......................................
Post-modification inspections (new action), per                        2              65             (1)           2 130             164         221,320
 inspection cycle.......................................
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ None.
\2\ Per inspection cycle.

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 39-11616 (65 FR 12077, March 8, 2000), and adding 
the following new airworthiness directive (AD):

2006-12-13 Airbus: Amendment 39-14639. Docket No. FAA-2004-19002; 
Directorate Identifier 2003-NM-27-AD.

Effective Date

    (a) This AD becomes effective July 18, 2006.

Affected ADs

    (b) This AD supersedes AD 2000-05-07, amendment 39-11616.

Applicability

    (c) This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes, as identified in Airbus 
Service Bulletin A300-57A0234, Revision 05, dated February 19, 2002; 
and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-
605R, F4-622R, and C4-605R Variant F airplanes, as identified in 
Airbus Service Bulletin A300-57A6087, Revision 04, dated February 
19, 2002; except airplanes on which Airbus Modification 11912 or 
11932 has been installed; certificated in any category.

Unsafe Condition

    (d) This AD was prompted by new service information that was 
issued by the manufacturer and mandated by the French airworthiness 
authority. We are issuing this AD to prevent fatigue cracking of the 
main landing gear (MLG) attachment fittings, which could result in 
reduced structural integrity of the airplane.

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.

Restatement of the Requirements of AD 2000-05-07

Repetitive Inspections

    (f) Perform a detailed inspection and a high-frequency eddy 
current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG 
attachment fittings at the lower flange, in accordance with the 
Accomplishment Instructions of any applicable service bulletin 
listed in Table 1 and Table 2 of this AD, at the time specified in 
paragraph (f)(1) or (f)(2) of this AD. After April 12, 2000 (the 
effective date of AD 2000-05-07), only the service bulletins listed 
in Table 2 of this AD may be used. Repeat the inspections thereafter 
at intervals not to exceed 1,500 flight cycles, until paragraph (h), 
(i), or (k) of this AD is accomplished.

                                   Table 1.--Revision 01 of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                           Airbus Service
                  Model                       Bulletin     Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4-     A300-57-6087              01  March 11, 1998.
 605R, B4-622R, F4-605R, F4-622R, and
 A300 C4-605R Variant F airplanes.

[[Page 33997]]

 
A300 B2 and A300 B4 series airplanes....     A300-57-0234              01  March 11, 1998.
----------------------------------------------------------------------------------------------------------------


                                Table 2.--Further Revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                           Airbus Service
                  Model                       Bulletin     Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4-     A300-57A6087             *02  June 24, 1999.
 605R, B4-622R, FA-605R, F4-622R, and
 A300 C4-605R Variant F airplanes.
                                          ...............             *03  May 19, 2000.
                                          ...............             *04  February 19, 2002.
A300 B2 and A300 B4 series airplanes....     A300-57A0234              02  June 24, 1999.
                                          ...............             *03  September 2, 1999.
                                          ...............             *04  May 19, 2000.
                                          ...............             *05  February 19, 2002.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.

    (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, amendment 39-10298): Inspect within 500 flight cycles after 
March 9, 1998.
    (2) For airplanes that have accumulated less than 20,000 total 
flight cycles as of March 9, 1998: Inspect prior to the accumulation 
of 18,000 total flight cycles, or within 1,500 flight cycles after 
March 9, 1998, whichever occurs later.

    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''


    Note 2: Accomplishment of the initial detailed and HFEC 
inspections in accordance with Airbus Service Bulletin A300-57A0234 
or A300-57A6087, both dated August 5, 1997, as applicable, is 
considered acceptable for compliance with the initial inspections 
required by paragraph (f) of this AD.

Repair

    (g) If any crack is detected during any inspection required by 
paragraph (f) of this AD, prior to further flight, accomplish the 
requirements of paragraph (g)(1) or (g)(2) of this AD, as 
applicable.
    (1) If a crack is detected at one hole only, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin in Table 2 of this AD.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA, or the 
European Aviation Safety Agency (EASA) (or its delegated agent).

Terminating Modification

    (h) Prior to the accumulation of 21,000 total flight cycles, or 
within 2 years after October 20, 1999 (the effective date of AD 99-
19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib 
5 of the MLG attachment fittings at the lower flange in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin in Table 3 of this AD. After the effective date of this AD, 
only Revision 04 of Airbus Service Bulletin A300-57-6088, and 
Revisions 04 and 05 of Airbus Service Bulletin A300-57-0235 may be 
used. Accomplishment of this modification constitutes terminating 
action for the repetitive inspection requirements of paragraphs (f) 
and (i) of this AD.

                            Table 3.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                                           Airbus Service
                  Model                       Bulletin     Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4-     A300-57-6088          \*\ 01  February 1, 1999.
 605R, B4-622R, F4-605R, F4-622R, A300
 C4-605R Variant F airplanes.
                                          ...............              02  September 5, 2002.
                                          ...............              04  December 3, 2003.
A300 B2 and A300 B4 series airplanes....     A300-57-0235          \*\ 01  February 1, 1999.
                                          ...............              03  September 5, 2002.
                                          ...............              04  March 13, 2003.
                                          ...............              05  December 3, 2003.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.


    Note 3: Accomplishment of the modification required by paragraph 
(h) of this AD prior to April 12, 2000, in accordance with Airbus 
Service Bulletin A300-57-6088 or A300-57-0235, both dated August 5, 
1998; as applicable; is acceptable for compliance with the 
requirements of that paragraph.

New Requirements of This AD

New Repetitive Inspections

    (i) For airplanes on which the modification specified in 
paragraph (h) or (k) of this AD has not been done as of the 
effective date of this AD, perform a detailed and an HFEC inspection 
to detect cracks of the lower flange of Gear Rib 5 of the MLG at 
holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the 
applicable service bulletin listed in Table 4 of this AD. Perform 
the inspections at the applicable time specified in paragraph 
(i)(1), (i)(2), (i)(3), or (i)(4) of this AD. Repeat the inspections 
thereafter at intervals not to exceed 700 flight cycles until the 
terminating modification required by paragraph (k) of this AD is 
accomplished. Accomplishment of the inspections per paragraph (i) of 
this AD,

[[Page 33998]]

terminates the inspection requirements of paragraph (f) of this AD.

                             Table 4.--Service Bulletins for Repetitive Inspections
----------------------------------------------------------------------------------------------------------------
                                           Airbus Service
                  Model                       Bulletin     Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4-     A300-57A6087          \*\ 04  February 19, 2002.
 605R, B4-622R, F4-605R, F4-622R, and C4-
 605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-       A300-57A0234          \*\ 05  February 19, 2002.
 2C, B4-103, and B4-203 airplanes.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.

    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; 
and Model C4-605R Variant F airplanes that have accumulated 18,000 
or more total flight cycles as of the effective date of this AD: 
Within 700 flight cycles after the effective date of this AD.
    (2) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes 
that have accumulated less than 18,000 total flight cycles as of the 
effective date of this AD: Prior to the accumulation of 18,000 total 
flight cycles, or within 700 flight cycles after the effective date 
of this AD, whichever occurs later.
    (3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have 
accumulated less than 18,000 total flight cycles as of the effective 
date of this AD: Prior to the accumulation of 14,500 total flight 
cycles, or within 700 flight cycles after the effective date of this 
AD, whichever occurs later.
    (4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes that have 
accumulated less than 18,000 total flight cycles as of the effective 
date of this AD: Prior to the accumulation of 11,600 total flight 
cycles, or within 700 flight cycles after the effective date of this 
AD, whichever occurs later.

Crack Repair

    (j) If any crack is detected during any inspection required by 
paragraph (i) of this AD, prior to further flight, accomplish the 
requirements of paragraph (j)(1) and (j)(2) of this AD, as 
applicable.
    (1) If a crack is detected at only one hole, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with Airbus Service Bulletin A300-57A0234, Revision 05, including 
Appendix 01, dated February 19, 2002 (for Model A300 B2-1A, B2-1C, 
B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-
57A6087, Revision 04, including Appendix 01, dated February 19, 2002 
(for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R airplanes); as applicable.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, or the EASA (or its delegated agent).

Terminating Modification

    (k) For airplanes on which the terminating modification in 
paragraph (h) of this AD has not been accomplished before the 
effective date of this AD: At the earlier of the times specified in 
paragraphs (k)(1) and (k)(2) of this AD, modify Gear Rib 5 of the 
MLG attachment fittings at the lower flange. Except as provided by 
paragraph letter (l) of this AD, do the modification in accordance 
with the applicable service bulletin in Table 5 of this AD. This 
action terminates the repetitive inspections requirements of 
paragraphs (f) and (i) of this AD.
    (1) Prior to the accumulation of 21,000 total flight cycles, or 
within 2 years after October 20, 1999, whichever is later.
    (2) Within 16 months after the effective date of this AD.

                            Table 5.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                                           Airbus Service
                  Model                       Bulletin     Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, B4-     A300-57-6088              04  December 3, 2003.
 605R, B4-622R, F4-605R, F4-622R, and C4-
 605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-       A300-57-0235              04  March 13, 2003.
 2C, B4-103, and B4-203 05 2003                                        05  December 3, 2003.
 airplanes.
----------------------------------------------------------------------------------------------------------------

    (l) Where the applicable service bulletin in paragraph (k) of 
this AD specifies to contact Airbus for modification instructions; 
or if there is a previously installed repair at any of the affected 
fastener holes; or if a crack is found when accomplishing the 
modification: Prior to further flight, modify in accordance with a 
method approved by the Manager, International Branch, ANM-116, or 
the EASA (or its delegated agent).

Post-Modification Inspections

    (m) Within 700 flight cycles after doing the modification in 
accordance with paragraph (h), (k), or (l) of this AD, or within 6 
months after the effective date of this AD, whichever occurs later, 
except as provided by paragraph (o) of this AD: Do a detailed and an 
HFEC inspection for cracks at holes 47 and 54 in the lower flange of 
Gear Rib 5, and do all related investigative and corrective actions 
before further flight, by doing all the actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A300-57A0246, 
including Appendix 01, dated May 20, 2005; or Airbus Service 
Bulletin A300-57A6101, including Appendix 01, dated May 20, 2005; as 
applicable. Where the applicable service bulletin specifies to 
contact Airbus for repair instructions: Prior to further flight, 
modify in accordance with a method approved by the Manager, 
International Branch, ANM-116, or the EASA (or its delegated agent). 
Repeat the inspection and related investigative and corrective 
actions thereafter at intervals not to exceed 700 flight cycles. If 
no crack is detected during the repeat inspection performed at or 
above 2,100 flight cycles after doing the modification in accordance 
with paragraph (h), (k), or (l) of this AD, then no further 
inspection is required. Except, at least one inspection is required 
after the accumulation of 2,100 flight cycles after installing the 
modification in accordance with paragraph (h) or (k) of this AD.

Actions Accomplished Per Previous Issues of the Service Bulletins

    (n) Actions accomplished before the effective date of this AD, 
per the service bulletins listed in Table 6 of this AD, are 
considered acceptable for compliance with the corresponding action 
specified in this AD.

[[Page 33999]]



             Table 6.--Previous Issues of Service Bulletins
------------------------------------------------------------------------
   Airbus Service Bulletin    Revision level             Date
------------------------------------------------------------------------
A300-57-0235................          \*\ 02  September 27, 1999.
                                          03  September 5, 2002.
A300-57-6088................              02  September 5, 2000.
                                          03  March 13, 2003.
------------------------------------------------------------------------
* Including Appendix 01.

Reporting

    (o)(1) Although Airbus Service Bulletins A300-57A0234, A300-57-
0235, A300-57A6087, A300-57-6088, A300-57A0246, and A300-57A6101, 
specify to submit certain information to the manufacturer, this AD 
does not include such a requirement, except as provided by paragraph 
(o)(2) of this AD.
    (2) Where Airbus Service Bulletins A300-57A0246 and A300-57A6101 
specify to submit a report of positive and negative findings of the 
post-modification inspection required by paragraph (m) of this AD, 
within 30 days after the effective date of this AD, submit a report 
only of the positive findings of post-modification inspections to 
Airbus, Customer Service Directorate, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France. The report must include the inspection 
results, a description of any discrepancies found, the airplane 
serial number, and the number of landings and flight hours on the 
airplane. Under the provisions of the Paperwork Reduction Act of 
1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget 
(OMB) has approved the information collection requirements contained 
in this AD and has assigned OMB Control Number 2120-0056.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) 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.
    (3) AMOCs approved previously per AD 2000-05-07 are approved as 
AMOCs with this AD.

Related Information

    (q) French airworthiness directives 2003-318(B), dated August 
20, 2003; and F-2005-113 R1, dated July 20, 2005; also address the 
subject of this AD.

Material Incorporated by Reference

    (r) You must use the service information listed in Table 7 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

                                  Table 7.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Airbus Service Bulletin                   Revision level                          Date
----------------------------------------------------------------------------------------------------------------
A300-57A0234.............................   02..........................  June 24, 1999.
A300-57A0234.............................  * 03.........................  September 2, 1999.
A300-57A0234.............................  * 04.........................  May 19, 2000.
A300-57A0234.............................  * 05.........................  February 19, 2002.
A300-57A0246.............................  Original *...................  May 20, 2005.
A300-57A6087.............................  * 02.........................  June 24, 1999.
A300-57A6087.............................  * 03.........................  May 19, 2000.
A300-57A6087.............................  * 04.........................  February 19, 2002.
A300-57A6101.............................  Original *...................  May 20, 2005.
A300-57-0234.............................   01..........................  March 11, 1998.
A300-57-0235.............................  * 01.........................  February 1, 1999.
A300-57-0235.............................   03..........................  September 5, 2002.
A300-57-0235.............................   04..........................  March 13, 2003.
A300-57-0235.............................   05..........................  December 3, 2003.
A300-57-6087.............................   01..........................  March 11, 1998.
A300-57-6088.............................  * 01.........................  February 1, 1999.
A300-57-6088.............................   02..........................  September 5, 2002.
A300-57-6088.............................   04..........................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.

    (1) The Director of the Federal Register approved the 
incorporation by reference of the documents listed in Table 8 of 
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

                                Table 8.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Airbus Service Bulletin                   Revision level                          Date
----------------------------------------------------------------------------------------------------------------
A300-57A0234.............................  * 04.........................  May 19, 2000.
A300-57A0234.............................  * 05.........................  February 19, 2002.
A300-57A0246.............................  Original *...................  May 20, 2005.
A300-57A6087.............................  * 03.........................  May 19, 2000.
A300-57A6087.............................  * 04.........................  February 19, 2002.
A300-57A6101.............................  Original *...................  May 20, 2005.
A300-57-0235.............................   03..........................  September 5, 2002.
A300-57-0235.............................   04..........................  March 13, 2003.

[[Page 34000]]

 
A300-57-0235.............................   05..........................  December 3, 2003.
A300-57-6088.............................   02..........................  September 5, 2002.
A300-57-6088.............................   04..........................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------
* Including Appendix 01.

    (2) On April 12, 2000 (65 FR 12077, March 8, 2000), the Director 
of the Federal Register approved the incorporation by reference of 
the documents listed in Table 9 of this AD.

         Table 9.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
   Airbus Service Bulletin    Revision level             Date
------------------------------------------------------------------------
A300-57A0234................              02  June 24, 1999.
A300-57A0234................            * 03  September 2, 1999.
A300-57A6087................            * 02  June 24, 1999.
------------------------------------------------------------------------
* Including Appendix 01.

    (3) On October 20, 1999 (64 FR 49966, September 15, 1999), the 
Director of the Federal Register approved the incorporation by 
reference of the documents listed in Table 10 of this AD.

        Table 10.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
   Airbus Service Bulletin    Revision level             Date
------------------------------------------------------------------------
A300-57-0234................              01  March 11, 1998.
A300-57-0235................            * 01  February 1, 1999.
A300-57-6087................              01  March 11, 1998.
A300-57-6088................            * 01  February 1, 1999.
------------------------------------------------------------------------
* Including Appendix 01.

    (4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on May 31, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-5244 Filed 6-12-06; 8:45 am]
BILLING CODE 4910-13-P