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), 15068-15073 [E6-4402]

Download as PDF 15068 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules 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. Related Information (k) French airworthiness directive F–2006– 011 R1, dated January 18, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on March 13, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–4409 Filed 3–24–06; 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] 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) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. sroberts on PROD1PC70 with PROPOSALS AGENCY: SUMMARY: The FAA is revising an earlier NPRM for an airworthiness directive (AD) that applies to certain Airbus Model A300 B2 and A300 B4 series airplanes, and A300–600 series airplanes. The original NPRM would have superseded an existing AD that currently requires repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower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. The original NPRM proposed to reduce the compliance times for all inspections, and require doing the inspections in accordance with new revisions of the service bulletins. The original NPRM resulted from new service information that was issued by the manufacturer and mandated by the French airworthiness authority. This new action revises the VerDate Aug<31>2005 18:28 Mar 24, 2006 Jkt 208001 original NPRM by proposing new repetitive inspections of certain areas of the attachment fittings that were repaired in accordance with the actions specified in both the existing AD and the original NPRM. We are proposing this supplemental NPRM to prevent fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this supplemental NPRM by April 21, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 proposed AD. For Model A300 600 series airplanes, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed 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: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposal. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2004–19002; Directorate Identifier 2003–NM–27–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 consider all comments received by the closing date and may amend this supplemental NPRM in light of those comments. We will post all comments submitted, without change, to https://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://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 DOT street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with a notice of proposed rulemaking (the original NPRM) for an AD for certain Airbus Model A300 B2 and A300 B4 series airplanes; and Model A300–600 series airplanes. The original NPRM proposed to supersede AD 2000–05–07, amendment 39–11616 (65 FR 12077, March 8, 2000), which applies to certain Airbus Model A300 and A300–600 series airplanes. The original NPRM was published in the Federal Register on September 7, 2004 (69 FR 54063). The original NPRM proposed to reduce the compliance times for all inspections required by AD 2000–05–07, and to require inspections in accordance with new revisions of the service bulletins. The original NPRM resulted from new service information that was issued by the manufacturer and mandated by the French airworthiness authority. We proposed the original NPRM to prevent fatigue cracking of the main landing gear (MLG) attachment fittings, which could result in reduced structural integrity of the airplane. E:\FR\FM\27MRP1.SGM 27MRP1 15069 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules Actions Since Original NPRM Was Issued Since we issued the original NPRM, we have received reports of cracks on airplanes that were modified in accordance with Airbus Service Bulletin A300–57–0235, Revisions 01 through 05; and Airbus Service Bulletin A300– 57–6088, Revisions 01 through 04. These service bulletins were cited in both the original NPRM and in AD 2000–05–07 as the appropriate sources of service information for modifying Gear Rib 5 of the MLG attachment fittings at the lower flange. The manufacturer has indicated that the reported cracks may have existed previously, but were probably missed during the installation of the modification because of improper inspection during installation, or because not enough material was removed during the spotfacing operation. The manufacturer has now issued two new service bulletins, described below, which provide procedures for inspecting the modified airplanes to ensure that the inspection area is crack-free. Relevant Service Information Airbus has issued the service bulletins identified in the following table. NEW AIRBUS SERVICE BULLETINS Airbus service bulletin A300–600 ........................................ A300 B2 and A300 B4 .................... sroberts on PROD1PC70 with PROPOSALS Model A300–57A6101, including Appendix 01 ................................................ A300–57A0246, including Appendix 01 ................................................ The service bulletins describe procedures for doing repetitive detailed visual inspections for cracks of the bottom flange and the vertical web in the area between the wing rear spar/gear rib 5 attachment, and the forward reaction-rod pickup lug. On the inboard side, this inspection includes inspecting for cracks of the areas around all fasteners, particularly at holes 47 and 54. On the outboard side, this inspection includes inspecting for cracks of the lower flange, the vertical web, and the areas around all fasteners. If any crack is found during this inspection, the service bulletins specify that operators should measure the length of the crack and contact the manufacturer for repair instructions. If no crack is found during the detailed visual inspection, the service bulletins provide procedures for related investigative and corrective actions. The related investigative action is doing a high-frequency eddy current inspection for cracks of holes 47 and 54. If any crack is found, the corrective action is to contact the manufacturer for repair instructions. If no crack is found, the corrective action is to install new nuts at holes 47 and 54. The service bulletins also give instructions for reporting all inspection findings, including nil findings, to the manufacturer. The service bulletins specify that the detailed visual inspection is to be repeated at intervals not to exceed 700 flight cycles. If no crack is found during the inspection performed at or above 2,100 flight cycles after modifying Gear Rib 5 of the MLG attachment fittings at the lower flange, the service bulletins specify that no further action is necessary. ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, mandated the service information and VerDate Aug<31>2005 18:28 Mar 24, 2006 Jkt 208001 Date issued French airworthiness directive F–2005–113 R1, dated July 20, 2005, to ensure the continued airworthiness of these airplanes in France. Comments We have considered the following comments on the original NPRM. Support for the Proposed AD One commenter supports the original NPRM as proposed. Request To Extend Compliance Time for Modification One commenter requests that the compliance time for the proposed modification of Gear Rib 5 of the MLG attachment fittings be extended from 15 months to 30 months. The commenter states that the request to extend the compliance time is justified because the repetitive interval has been shortened to 700 flight cycles. According to the commenter, the manner in which this crack is expected to grow means that it will not reach an un-repairable length during the inspection interval. Therefore, the operator states that the time needed to complete the modification should be extended to 30 months to fit the heavy maintenance schedule for all operators. The commenter considers that the adoption of the proposed compliance time of 15 months would require operators to schedule special visits to do the repair, at additional expense and downtime. We do not agree with the commenter’s request to extend the compliance time from 15 months to 30 months. In developing an appropriate compliance time for this action, we considered the urgency associated with the subject unsafe condition, and the practical aspect of accomplishing the required modification within a period of time that corresponds to the normal PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 May 20, 2005. May 20, 2005. scheduled maintenance for most affected operators. In addition, because operators’ schedules vary substantially, we cannot accommodate every operator’s optimal scheduling in each AD. However, according to the provisions of paragraph (p) of this supplemental NPRM, we may approve requests to adjust the compliance time if the request includes data that prove that the new compliance time would provide an acceptable level of safety. In addition, based on further evaluation of French airworthiness directive 2003–318(B), dated August 20, 2003, we have extended the compliance time for the proposed modification of Gear Rib 5 of the MLG attachment fittings from 15 months to 16 months. This compliance time parallels the compliance time in the French airworthiness directive. Request To Revise Cost Estimate The commenter requests that we revise the cost estimate to between 82 and 100 work hours for the modification of gear rib 5. The commenter states that Airbus Service Bulletin A300–57–6088, Revision 04, dated December 3, 2003, includes an estimate of 82 work hours to do this modification. The commenter also states that, in its experience, this modification takes approximately 100 work hours, depending on the difficulty in removing the fasteners. The commenter further states that the need to do the modification during special visits will increase the cost to operators. We partially agree with the commenter’s request. After further analysis of the service information, we agree that the work hours to do the modification as provided in Airbus Service Bulletin A300–57–6088, Revision 04, are higher than the work hours in the original NPRM. The cost information, below, has been revised to E:\FR\FM\27MRP1.SGM 27MRP1 15070 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules indicate this higher amount. We disagree with the request to revise the work hours to between 82 and 100 work hours. We consider in our cost estimates only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. We have made no further change to this supplemental NPRM regarding this issue. Explanation of Change in Applicability We have revised the applicability to identify model designations as published in the most recent type certificate data sheet for the affected models. Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. Explanation of Change to Service Bulletin Reference We have revised the applicability to correct a reference to Airbus Service Bulletin A300–57A6087. This service bulletin was inadvertently referred to in the original NPRM as Airbus Service Bulletin A300–75A6087. consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the DGAC approve would be acceptable for compliance with this proposed AD. FAA’s Determination and Proposed Requirements of the Supplemental NPRM The changes discussed above expand the scope of the original NPRM; therefore, we have determined that it is necessary to reopen the comment period to provide additional opportunity for public comment on this supplemental NPRM. In this supplemental NPRM, the ‘‘detailed visual inspection’’ specified in the Airbus service bulletins and in the French airworthiness directives, is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the supplemental NPRM. Difference Between the Supplemental NPRM and Airbus Service Bulletins A300–57A0246 and A300–57A6101 Airbus Service Bulletins A300– 57A0246 and A300–57A6101 specify to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions using a method that we or the DGAC (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and Clarification of Inspection Terminology Explanation of Reporting Requirement This proposed AD also specifies that operators report to the manufacturer any positive findings of cracks during the post-modification inspections. These inspection reports will help determine the extent of the cracking in the affected fleet. Based on the results of these reports, we may determine that further corrective action is warranted. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Action Modification (required by AD 2000– 05–07). Pre-modification inspections (new proposed action), per inspection cycle. Post-modification inspections (new proposed action), per inspection cycle. sroberts on PROD1PC70 with PROPOSALS Jkt 208001 Number of U.S.-registered airplanes Cost per airplane Fleet cost $65 $10,270 $14,820 164 $2,430,480 6 65 None 390 164 $63,960, per inspection cycle. 2 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 18:28 Mar 24, 2006 Parts 70 Authority for This Rulemaking VerDate Aug<31>2005 Average labor rate per hour Work hours 65 None 130 164 $21,320, per inspection cycle. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this supplemental NPRM 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, Safety. E:\FR\FM\27MRP1.SGM 27MRP1 15071 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules Affected ADs The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): which could result in reduced structural integrity of the airplane. (b) This AD supersedes AD 2000–05–07, amendment 39–11616. Compliance Applicability (c) This AD applies to 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 Varian 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 Airbus: Docket No. FAA–2004–19002; Directorate Identifier 2003–NM–27–AD. Comments Due Date (a) The FAA must receive comments on this AD action by April 21, 2006. (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, (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 Model Airbus service bulletin Revision level Date 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 B2 and A300 B4 series airplanes .................... A300–57–6087 ............ 01 ......................................................... March 11, 1998. A300–57–0234 ............ 01 ......................................................... March 11, 1998. TABLE 2.—FURTHER REVISIONS OF SERVICE BULLETINS 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 B2 and A300 B4 series airplanes .................... sroberts on PROD1PC70 with PROPOSALS Model A300–57A6087 ........... (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 VerDate Aug<31>2005 20:46 Mar 24, 2006 Jkt 208001 A300–57A0234 ........... Revision level 02, 03, 04, 02, 03, 04, 05, including including including including including including including Appendix Appendix Appendix Appendix Appendix Appendix Appendix 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 paragraphs (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. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 01 01 01 01 01 01 01 Date ................... ................... ................... ................... ................... ................... ................... June 24, 1999. May 19, 2000. February 19, 2002. June 24, 1999. September 2, 1999. May 19, 2000. February 19, 2002. (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 ´ ´ Direction Generale de l’Aviation Civile (DGAC) (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 E:\FR\FM\27MRP1.SGM 27MRP1 15072 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules 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 Revision level 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 B2 and A300 B4 ............................................... A300–57–6088 ............ 01, including Appendix 01 ................... 02 ......................................................... 04 ......................................................... 01, including Appendix 01 ................... 03 ......................................................... 04 ......................................................... 05 ......................................................... Note 3: Accomplishment of the modification required by paragraph (h) of this AD prior to April 12, 2000 (the effective date of AD 2000–05–07), 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. A300–57–0235 ............ 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 Date February 1, 1999. September 5, 2002. December 3, 2003. February, 1, 1999. September 5, 2002. March 13, 2003. December 3, 2003. 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, terminates the inspection requirements of paragraph (f) of this AD. TABLE 4.—SERVICE BULLETINS FOR REPETITIVE INSPECTIONS Airbus service bulletin Revision level 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. sroberts on PROD1PC70 with PROPOSALS Model A300–57A6087 ........... 04, including Appendix 01 ................... February 19, 2002. A300–57A0234 ........... 05, including Appendix 01 ................... February 19, 2002. (1) For Model A300 B2–1A, B2–1C, B2K– 3C, B2–203, B4–2C, B4–103, and B4–203 airplanes; A300 B4–600, B4–600R, and F4– 600R series 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 VerDate Aug<31>2005 20:46 Mar 24, 2006 Jkt 208001 Date 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 DGAC (or its delegated agent). Crack Repair Terminating Modification (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. PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 E:\FR\FM\27MRP1.SGM 27MRP1 15073 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules TABLE 5.—SERVICE BULLETINS FOR TERMINATING MODIFICATION Model Airbus service bulletin Revision level 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. A300–57–6088 ............ 04 ......................................................... December 3, 2003. A300–57–0235 ............ 04 ......................................................... 05 ......................................................... March 13, 2003. December 3, 2003. (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 DGAC (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 DGAC (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 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. TABLE 6.—PREVIOUS ISSUES OF SERVICE BULLETINS Airbus service bulletin Revision level A300–57–0235 ................................................... 02, including Appendix 01 ............................... 03 ..................................................................... 02 ..................................................................... 03 ..................................................................... A300–57–6088 ................................................... sroberts on PROD1PC70 with PROPOSALS 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, both dated May 20, 2005, specify to submit a report of positive and negative findings of the postmodification 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 postmodification 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. VerDate Aug<31>2005 20:46 Mar 24, 2006 Jkt 208001 Date September 27, 1999. September 5, 2002. September 5, 2000. March 13, 2003. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (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. Federal Aviation Administration 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. Issued in Renton, Washington, on March 9, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–4402 Filed 3–24–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 14 CFR Part 39 [Docket No. FAA–2005–22524; Directorate Identifier 2005–NM–135–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, A340–200, and A340–300 Series Airplanes, and Model A340–541 and A340–642 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: The FAA is revising an earlier NPRM for an airworthiness directive (AD) that would have applied to certain Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes, and A340–541 and A340–642 airplanes. The original NPRM would have required inspecting to determine if certain emergency escape slides/slide E:\FR\FM\27MRP1.SGM 27MRP1

Agencies

[Federal Register Volume 71, Number 58 (Monday, March 27, 2006)]
[Proposed Rules]
[Pages 15068-15073]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-4402]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-27-AD]
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: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.

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

SUMMARY: The FAA is revising an earlier NPRM for an airworthiness
directive (AD) that applies to certain Airbus Model A300 B2 and A300 B4
series airplanes, and A300-600 series airplanes. The original NPRM
would have superseded an existing AD that 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. The original NPRM proposed to reduce the
compliance times for all inspections, and require doing the inspections
in accordance with new revisions of the service bulletins. The original
NPRM resulted from new service information that was issued by the
manufacturer and mandated by the French airworthiness authority. This
new action revises the original NPRM by proposing new repetitive
inspections of certain areas of the attachment fittings that were
repaired in accordance with the actions specified in both the existing
AD and the original NPRM. We are proposing this supplemental NPRM to
prevent fatigue cracking of the MLG attachment fittings, which could
result in reduced structural integrity of the airplane.

DATES: We must receive comments on this supplemental NPRM by April 21,
2006.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
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 proposed AD. For Model A300 600
series airplanes, contact Airbus, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France, for service information identified in this
proposed 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:

Comments Invited

We invite you to submit any relevant written data, views, or
arguments regarding this proposal. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2004-19002; Directorate Identifier 2003-NM-27-AD'' at the beginning
of your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of this
supplemental NPRM. We will consider all comments received by the
closing date and may amend this supplemental NPRM in light of those
comments.
We will post all comments submitted, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at https://
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 DOT
street address stated in ADDRESSES. Comments will be available in the
AD docket shortly after the Docket Management System receives them.

Discussion

We proposed to amend part 39 of the Federal Aviation Regulations
(14 CFR part 39) with a notice of proposed rulemaking (the original
NPRM) for an AD for certain Airbus Model A300 B2 and A300 B4 series
airplanes; and Model A300-600 series airplanes. The original NPRM
proposed to supersede AD 2000-05-07, amendment 39-11616 (65 FR 12077,
March 8, 2000), which applies to certain Airbus Model A300 and A300-600
series airplanes. The original NPRM was published in the Federal
Register on September 7, 2004 (69 FR 54063). The original NPRM proposed
to reduce the compliance times for all inspections required by AD 2000-
05-07, and to require inspections in accordance with new revisions of
the service bulletins. The original NPRM resulted from new service
information that was issued by the manufacturer and mandated by the
French airworthiness authority. We proposed the original NPRM to
prevent fatigue cracking of the main landing gear (MLG) attachment
fittings, which could result in reduced structural integrity of the
airplane.

[[Page 15069]]

Actions Since Original NPRM Was Issued

Since we issued the original NPRM, we have received reports of
cracks on airplanes that were modified in accordance with Airbus
Service Bulletin A300-57-0235, Revisions 01 through 05; and Airbus
Service Bulletin A300-57-6088, Revisions 01 through 04. These service
bulletins were cited in both the original NPRM and in AD 2000-05-07 as
the appropriate sources of service information for modifying Gear Rib 5
of the MLG attachment fittings at the lower flange. The manufacturer
has indicated that the reported cracks may have existed previously, but
were probably missed during the installation of the modification
because of improper inspection during installation, or because not
enough material was removed during the spotfacing operation. The
manufacturer has now issued two new service bulletins, described below,
which provide procedures for inspecting the modified airplanes to
ensure that the inspection area is crack-free.

Relevant Service Information

Airbus has issued the service bulletins identified in the following
table.

New Airbus Service Bulletins
------------------------------------------------------------------------
Airbus service
Model bulletin Date
------------------------------------------------------------------------
A300-600...................... A300-57A6101, May 20, 2005.
including Appendix 01.
A300 B2 and A300 B4........... A300-57A0246, May 20, 2005.
including Appendix 01.
------------------------------------------------------------------------

The service bulletins describe procedures for doing repetitive
detailed visual inspections for cracks of the bottom flange and the
vertical web in the area between the wing rear spar/gear rib 5
attachment, and the forward reaction-rod pickup lug. On the inboard
side, this inspection includes inspecting for cracks of the areas
around all fasteners, particularly at holes 47 and 54. On the outboard
side, this inspection includes inspecting for cracks of the lower
flange, the vertical web, and the areas around all fasteners. If any
crack is found during this inspection, the service bulletins specify
that operators should measure the length of the crack and contact the
manufacturer for repair instructions.
If no crack is found during the detailed visual inspection, the
service bulletins provide procedures for related investigative and
corrective actions. The related investigative action is doing a high-
frequency eddy current inspection for cracks of holes 47 and 54. If any
crack is found, the corrective action is to contact the manufacturer
for repair instructions. If no crack is found, the corrective action is
to install new nuts at holes 47 and 54.
The service bulletins also give instructions for reporting all
inspection findings, including nil findings, to the manufacturer. The
service bulletins specify that the detailed visual inspection is to be
repeated at intervals not to exceed 700 flight cycles. If no crack is
found during the inspection performed at or above 2,100 flight cycles
after modifying Gear Rib 5 of the MLG attachment fittings at the lower
flange, the service bulletins specify that no further action is
necessary.
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, mandated the service
information and issued French airworthiness directive F-2005-113 R1,
dated July 20, 2005, to ensure the continued airworthiness of these
airplanes in France.

Comments

We have considered the following comments on the original NPRM.

Support for the Proposed AD

One commenter supports the original NPRM as proposed.

Request To Extend Compliance Time for Modification

One commenter requests that the compliance time for the proposed
modification of Gear Rib 5 of the MLG attachment fittings be extended
from 15 months to 30 months. The commenter states that the request to
extend the compliance time is justified because the repetitive interval
has been shortened to 700 flight cycles. According to the commenter,
the manner in which this crack is expected to grow means that it will
not reach an un-repairable length during the inspection interval.
Therefore, the operator states that the time needed to complete the
modification should be extended to 30 months to fit the heavy
maintenance schedule for all operators. The commenter considers that
the adoption of the proposed compliance time of 15 months would require
operators to schedule special visits to do the repair, at additional
expense and downtime.
We do not agree with the commenter's request to extend the
compliance time from 15 months to 30 months. In developing an
appropriate compliance time for this action, we considered the urgency
associated with the subject unsafe condition, and the practical aspect
of accomplishing the required modification within a period of time that
corresponds to the normal scheduled maintenance for most affected
operators. In addition, because operators' schedules vary
substantially, we cannot accommodate every operator's optimal
scheduling in each AD. However, according to the provisions of
paragraph (p) of this supplemental NPRM, we may approve requests to
adjust the compliance time if the request includes data that prove that
the new compliance time would provide an acceptable level of safety.
In addition, based on further evaluation of French airworthiness
directive 2003-318(B), dated August 20, 2003, we have extended the
compliance time for the proposed modification of Gear Rib 5 of the MLG
attachment fittings from 15 months to 16 months. This compliance time
parallels the compliance time in the French airworthiness directive.

Request To Revise Cost Estimate

The commenter requests that we revise the cost estimate to between
82 and 100 work hours for the modification of gear rib 5. The commenter
states that Airbus Service Bulletin A300-57-6088, Revision 04, dated
December 3, 2003, includes an estimate of 82 work hours to do this
modification. The commenter also states that, in its experience, this
modification takes approximately 100 work hours, depending on the
difficulty in removing the fasteners. The commenter further states that
the need to do the modification during special visits will increase the
cost to operators.
We partially agree with the commenter's request. After further
analysis of the service information, we agree that the work hours to do
the modification as provided in Airbus Service Bulletin A300-57-6088,
Revision 04, are higher than the work hours in the original NPRM. The
cost information, below, has been revised to

[[Page 15070]]

indicate this higher amount. We disagree with the request to revise the
work hours to between 82 and 100 work hours. We consider in our cost
estimates only the time necessary to perform the specific actions
actually required by the AD. These figures typically do not include
incidental costs, such as the time required to gain access and close
up, planning time, or time necessitated by other administrative
actions. We have made no further change to this supplemental NPRM
regarding this issue.

Explanation of Change in Applicability

We have revised the applicability to identify model designations as
published in the most recent type certificate data sheet for the
affected models.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.

Explanation of Change to Service Bulletin Reference

We have revised the applicability to correct a reference to Airbus
Service Bulletin A300-57A6087. This service bulletin was inadvertently
referred to in the original NPRM as Airbus Service Bulletin A300-
75A6087.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

The changes discussed above expand the scope of the original NPRM;
therefore, we have determined that it is necessary to reopen the
comment period to provide additional opportunity for public comment on
this supplemental NPRM.

Difference Between the Supplemental NPRM and Airbus Service Bulletins
A300-57A0246 and A300-57A6101

Airbus Service Bulletins A300-57A0246 and A300-57A6101 specify to
contact the manufacturer for instructions on how to repair certain
conditions, but this proposed AD would require repairing those
conditions using a method that we or the DGAC (or its delegated agent)
approve. In light of the type of repair that would be required to
address the unsafe condition, and consistent with existing bilateral
airworthiness agreements, we have determined that, for this proposed
AD, a repair we or the DGAC approve would be acceptable for compliance
with this proposed AD.

Clarification of Inspection Terminology

In this supplemental NPRM, the ``detailed visual inspection''
specified in the Airbus service bulletins and in the French
airworthiness directives, is referred to as a ``detailed inspection.''
We have included the definition for a detailed inspection in a note in
the supplemental NPRM.

Explanation of Reporting Requirement

This proposed AD also specifies that operators report to the
manufacturer any positive findings of cracks during the post-
modification inspections. These inspection reports will help determine
the extent of the cracking in the affected fleet. Based on the results
of these reports, we may determine that further corrective action is
warranted.

Costs of Compliance

The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification (required by AD 2000-05-07).. 70 $65 $10,270 $14,820 164 $2,430,480
Pre-modification inspections (new proposed 6 65 None 390 164 $63,960, per inspection
action), per inspection cycle. cycle.
Post-modification inspections (new 2 65 None 130 164 $21,320, per inspection
proposed action), per inspection cycle. 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this supplemental NPRM 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, Safety.

[[Page 15071]]

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-
27-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by April 21,
2006.

Affected ADs

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

Applicability

(c) This AD applies to 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 Varian 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
----------------------------------------------------------------------------------------------------------------
Model Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, A300-57-6087........... 01..................... March 11, 1998.
B4-605R, B4-622R, F4-605R, F4-622R,
and A300 C4-605R Variant F airplanes.
A300 B2 and A300 B4 series airplanes. A300-57-0234........... 01..................... March 11, 1998.
----------------------------------------------------------------------------------------------------------------

Table 2.--further revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Model Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, A300-57A6087........... 02, including Appendix June 24, 1999.
B4-605R, B4-622R, F4-605R, F4-622R, 01. May 19, 2000.
and A300 C4-605R Variant F airplanes. 03, including Appendix February 19, 2002.
01.
04, including Appendix
01.
A300 B2 and A300 B4 series airplanes. A300-57A0234........... 02, including Appendix June 24, 1999.
01.
03, including Appendix September 2, 1999.
01.
04, including Appendix May 19, 2000.
01.
05, including Appendix February 19, 2002.
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 paragraphs (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
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (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

[[Page 15072]]

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 Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, A300-57-6088........... 01, including Appendix February 1, 1999.
B4-605R, B4-622R, F4-605R, F4-622R, 01. September 5, 2002.
and A300 C4-605R Variant F airplanes. 02..................... December 3, 2003.
04.....................
A300 B2 and A300 B4.................. A300-57-0235........... 01, including Appendix February, 1, 1999.
01.
03..................... September 5, 2002.
04..................... March 13, 2003.
05..................... December 3, 2003.
----------------------------------------------------------------------------------------------------------------

Note 3: Accomplishment of the modification required by paragraph
(h) of this AD prior to April 12, 2000 (the effective date of AD
2000-05-07), 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, terminates the inspection requirements of paragraph (f) of
this AD.

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

(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes; A300 B4-600, B4-600R, and F4-600R series
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 DGAC (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.

[[Page 15073]]

Table 5.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
Model Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622, A300-57-6088........... 04..................... December 3, 2003.
B4-605R, 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 airplanes. 05..................... December 3, 2003.
----------------------------------------------------------------------------------------------------------------

(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 DGAC (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 DGAC (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.

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

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, both dated May 20, 2005, 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.

Issued in Renton, Washington, on March 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-4402 Filed 3-24-06; 8:45 am]
BILLING CODE 4910-13-P

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