Airworthiness Directives; Airbus Model A321-100 Series Airplanes, 32807-32811 [06-5121]

Download as PDF 32807 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations this rule, as stated above, this rule merely implements language which Congress has enacted and complies with the court’s final judgment and order. AMS is committed to compliance with the Government Paperwork Elimination Act (GPEA), which requires Government agencies in general to provide the public the option of submitting information or transacting business electronically to the maximum extent possible. USDA has not identified any relevant Federal rules that duplicate, overlap, or conflict with this rule. No additional collection or recordkeeping requirements are imposed on the public by this rule. Accordingly, OMB clearance is not required by § 305(h) of the Paperwork Reduction Act of 1995, 44 U.S.C. 3501, et seq., or OMB’s implementing regulation at 5 CFR part 1320. Further, given the Congressional amendments, and the court’s final judgment and order, good cause exists under 5 U.S.C. 533 for not postponing the effective date of this rule, except § 205.606, until 30 days after publication in the Federal Register. List of Subjects in 7 CFR Part 205 Administrative practice and procedure, Agriculture, Animals, Archives and records, Imports, Labeling, Organically produced products, Plants, Reporting and recordkeeping requirements, Seals and insignia, Soil conservation. I For the reasons set forth in the preamble, 7 CFR part 205, is amended as follows: PART 205—NATIONAL ORGANIC PROGRAM 1. The authority citation for 7 CFR part 205 continues to read as follows: I Authority: 7 U.S.C. 6501–6522. 2. Section 205.236 (a)(2) is revised to read as follows: I § 205.236 Origin of Livestock. (a) * * * (2) Dairy animals. Milk or milk products must be from animals that have been under continuous organic management beginning no later than 1 year prior to the production of the milk or milk products that are to be sold, labeled, or represented as organic, Except, (i) That, crops and forage from land, included in the organic system plan of a dairy farm, that is in the third year of organic management may be consumed by the dairy animals of the farm during the 12-month period immediately prior to the sale of organic milk and milk products; and (ii) That, when an entire, distinct herd is converted to organic production, the producer may, provided no milk produced under this subparagraph enters the stream of commerce labeled as organic after June 9, 2007: (a) For the first 9 months of the year, provide a minimum of 80-percent feed that is either organic or raised from land included in the organic system plan and managed in compliance with organic crop requirements; and (b) Provide feed in compliance with § 205.237 for the final 3 months. (iii) Once an entire, distinct herd has been converted to organic production, all dairy animals shall be under organic management from the last third of gestation. * * * * * I 3. Section 205.606 is revised to read as follows: § 205.606 Nonorganically produced agricultural products allowed as ingredients in or on processed products labeled as organic. Only the following nonorganically produced agricultural products may be used as ingredients in or on processed products labeled as ‘‘organic,’’ only in accordance with any restrictions specified in this section, and only when the product is not commercially available in organic form. (a) Cornstarch (native) (b) Gums—water extracted only (arabic, guar, locust bean, carob bean) (c) Kelp—for use only as a thickener and dietary supplement (d) Lecithin—unbleached (e) Pectin (high-methoxy) Dated: June 2, 2006. Barry L. Carpenter, Acting Administrator, Agricultural Marketing Service. [FR Doc. 06–5203 Filed 6–5–06; 9:14 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24953; Directorate Identifier 2006–NM–084–AD; Amendment 39–14628; AD 2006–04–11 R1] RIN 2120–AA64 Airworthiness Directives; Airbus Model A321–100 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is revising an existing airworthiness directive (AD) that applies to certain Airbus Model A321–111, –112, and –131 airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar; and repair, if necessary. That AD also provides for optional terminating action for the repetitive inspections, adds inspections of three additional mounting holes, and revises the thresholds for the currently required inspections. We issued that AD to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane. This new AD retains the requirements and revises the applicability of that AD. This AD results from the discovery of a typographical error in the applicability of that AD, which could cause the unsafe condition on an affected airplane to remain uncorrected. We are issuing this AD to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane. DATES: Effective June 22, 2006. The incorporation by reference of the publications specified in the following table, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 8, 2006 (71 FR 8792, February 21, 2006). sroberts on PROD1PC70 with RULES MATERIAL INCORPORATED BY REFERENCE Revision level Airbus service bulletin A320–57–1100, including Appendix 01 .............................................................................................................. A320–57–1100, including Appendices 01 and 02 .............................................................................................. A320–57–1101 .................................................................................................................................................... VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\07JNR1.SGM 07JNR1 (1) 03 03 Date July 28, 1997. January 16, 2003. July 30, 2003. 32808 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations MATERIAL INCORPORATED BY REFERENCE—Continued Revision level Airbus service bulletin A320–57–1101 .................................................................................................................................................... 04 Date November 22, 2004. 1 Original. The incorporation by reference of Airbus Service Bulletin A320–57–1101, Revision 02, dated October 25, 2001, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 21, 2004 (69 FR 17906, April 6, 2004). The incorporation by reference of Airbus Service Bulletin A320–57–1101, dated July 24, 1997, as listed in the regulations, was approved previously by the Director of the Federal Register as of December 18, 1998 (63 FR 66753, December 3, 1998). We must receive comments on this AD by August 7, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: sroberts on PROD1PC70 with RULES Discussion On February 9, 2006, we issued AD 2006–04–11, amendment 39–14492 (71 FR 8792, February 21, 2006), for certain Airbus Model A321–111, –112, and –131 airplanes. That AD requires repetitive inspections to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar; and repair, if necessary. That AD also provides for optional terminating action for the repetitive inspections, adds inspections of three additional mounting holes, and revises the thresholds for the currently required inspections. That AD resulted from manufacturer analysis of the fatigue and damage tolerance of the area surrounding certain mounting holes of the MLG. We issued that AD to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane. Actions Since Existing AD Was Issued Since we issued AD 2006–04–11, amendment 39–14492, a typographical error was discovered in the applicability of that AD, which could cause the unsafe condition on an affected airplane to remained uncorrected. The applicability of that AD states, ‘‘all manufacturer serial numbers (MSN), except MSN 364 and 365.’’ The correct reference should have been, ‘‘all manufacturer serial numbers (MSN), except MSN 364 and 385.’’ Clarification of No Reporting Requirement Airbus Service Bulletin A320–57– 1101, Revision 03, dated July 30, 2003, which also describes procedures for reporting inspection findings to Airbus, was inadvertently omitted from paragraph (m) of AD 2006–04–11, which specifies that we do not require reports of inspection findings. We have revised paragraph (m) of this AD to include Service Bulletin A320–57–1101, Revision 3. FAA’s Determination and Requirements of this AD This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. This new AD revises the applicability of AD 2006–04–11 by correcting the reference, ‘‘all manufacturer serial numbers (MSN), except MSN 364 and 365,’’ to read ‘‘all manufacturer serial numbers (MSN), except MSN 364 and 385.’’ This new AD also retains the requirements of AD 2006–04–11. Costs of Compliance The revisions made to this AD add no additional economic burden. The current costs for this AD are repeated for the convenience of affected operators, as follows: None of the airplanes affected by this action are on the U.S. Register. All airplanes included in the applicability of this AD currently are operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider that this AD is necessary to ensure that the unsafe condition is addressed in the event that any of these subject airplanes are imported and placed on the U.S. Register in the future. If an affected airplane is imported and placed on the U.S. Register in the future, it would require approximately 22 work hours to accomplish the required actions at an average labor rate of $65 per work hour. Based on these figures, the cost impact of this AD would be $1,430 per airplane. If an operator elects to accomplish the optional terminating action provided by this AD, it would take approximately 520 work hours to accomplish, at an average labor rate of $65 per work hour. The cost of required parts would be approximately $17,540 per airplane. Based on these figures, the cost impact of the optional terminating action would be $51,340 per airplane. FAA’s Determination of the Effective Date No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in E:\FR\FM\07JNR1.SGM 07JNR1 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations less than 30 days after it is published in the Federal Register. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to the address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2006–24953; Directorate Identifier 2006–NM–084–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. We will post all comments we receive, without change, to http:// 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 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 http://dms.dot.gov. 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 the 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 AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. sroberts on PROD1PC70 with RULES 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. List of Subjects in 14 CFR Part 39 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 I VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 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: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14492 (71 FR 8792, February 21, 2006), and adding the following new airworthiness directive (AD): I AD 2006–04–11 R1 Airbus: Amendment 39–14628. Docket No. FAA–2006–24953; Directorate Identifier 2006–NM–084–AD. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 32809 Effective Date (a) This AD becomes effective June 22, 2006. Affected ADs (b) This AD revises AD 2006–04–11. Applicability (c) This AD applies to Airbus Model A321– 111, –112, and –131 airplanes, certificated in any category; all manufacturer serial numbers (MSN), except MSN 364 and 385; and except for those airplanes that have received Airbus Modification 24977 in production. Unsafe Condition (d) This AD results from manufacturer analysis of the fatigue and damage tolerance of the area surrounding certain mounting holes of the main landing gear (MLG). The FAA is issuing this AD to detect and correct fatigue cracking on the inner rear spar of the wings, 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 Requirements of AD 2004– 07–15 Repetitive Inspections and Corrective Actions (f) Prior to the accumulation of 20,000 total flight cycles, or within 120 days after December 18, 1998 (the effective date of AD 98–25–05, amendment 39–10928), whichever occurs later, perform an ultrasonic inspection to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the MLG and the actuating cylinder anchorage fittings on the inner rear spar, in accordance with Airbus Service Bulletin A320–57–1101, dated July 24, 1997; or Revision 02, dated October 25, 2001. (1) If no cracking is detected, prior to further flight, repair the sealant in the inspected areas and repeat the ultrasonic inspections thereafter at intervals not to exceed 7,700 flight cycles, until paragraph (g), (i), or (k) of this AD is accomplished. (2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Optional Terminating Action (g) Accomplishment of visual and eddy current inspections to detect cracking in the area surrounding certain attachment holes of the forward pintle fittings of the MLG and the actuating cylinder anchorage fittings on the inner rear spar; follow-on corrective actions, as applicable; and rework of the attachment holes; in accordance with Airbus Service Bulletin A320–57–1100, including Appendix 01, dated July 28, 1997; or Revision 03, including Appendices 01 and 02, dated January 16, 2003; constitutes terminating action for the repetitive inspection requirements of this AD. Actions E:\FR\FM\07JNR1.SGM 07JNR1 32810 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations accomplished in accordance with Airbus Service Bulletin A320–57–1100, Revision 01, including Appendices 01 and 02, dated June 4, 1999; or Revision 02, including Appendices 01 and 02, dated October 25, 2001; are considered acceptable for compliance with the optional terminating action specified in this paragraph. If any cracking is detected during accomplishment of any inspection described in the service bulletin, and the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). Repetitive Inspections for Airplanes Not Previously Inspected Per Paragraph (f) (h) For airplanes on which the initial inspection required by paragraph (f) of this AD has not been accomplished as of April 21, 2004 (the effective date of AD 2004–07–15): Accomplish the inspection required by paragraph (f) of this AD, at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (g) or (k) of this AD is accomplished. Accomplishment of this paragraph eliminates the need to accomplish repetitive inspections at the intervals required by paragraph (f)(1) of this AD. (1) Prior to the accumulation of 20,000 total flight cycles. (2) Prior to the accumulation of 37,300 total flight hours, or within 120 days after April 21, 2004, whichever occurs later. Repetitive Inspections for Airplanes Previously Inspected Per Paragraph (f) (i) For airplanes on which the initial inspection required by paragraph (f) of this AD has been accomplished as of April 21, 2004, and no cracking was found: Do the next inspection at the earlier of the times specified in paragraphs (i)(1) and (i)(2) of this AD, and repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (g) or (k) of this AD is accomplished. Accomplishment of this paragraph terminates the repetitive inspections required by paragraph (f)(1) of this AD. (1) Within 7,700 flight cycles since the most recent inspection. (2) At the later of the times specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD: (i) Within 5,500 flight cycles or 10,200 flight hours since the most recent inspection, whichever occurs first. (ii) Within 120 days after April 21, 2004. Existing Repair (j) If any cracking is detected during any inspection required by paragraph (h) or (i) of this AD: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). New Requirements of This AD Initial and Repetitive Inspections (k) Within the applicable compliance times specified by paragraph (k)(1), (k)(2), or (k)(3) of this AD, perform an ultrasonic inspection for cracking of the attachment holes of the MLG pintle fittings in the inner rear spar in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 57–1101, Revision 03, dated July 30, 2003; or Revision 04, dated November 22, 2004. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (g) of this AD is accomplished. Accomplishment of this paragraph terminates the repetitive inspections required by paragraphs (f)(1), (h), and (i) of this AD. (1) For airplanes that have never been inspected in accordance with Airbus Service Bulletin A320–57–1101, dated July 24, 1997; or Revision 02, dated October 25, 2001: Before the accumulation of 20,000 total flight cycles or 37,300 total flight hours, whichever occurs first; or within 120 days after the effective date of this AD; whichever occurs later. (2) For airplanes previously inspected in accordance with Airbus Service Bulletin A320–57–1101, dated July 24, 1997; or Revision 02, dated October 25, 2001, that have accumulated less than 18,900 total flight cycles or 35,300 total flight hours as of the effective date of this AD: Within 5,500 flight cycles or 10,200 flight hours, whichever occurs first, after the previous inspection performed in accordance with Airbus Service Bulletin A320–57–1101, Revision 02, dated October 25, 2001; or within 120 days after the effective date of this AD; whichever occurs later. (3) For airplanes previously inspected in accordance with Airbus Service Bulletin A320–57–1101, dated July 24, 1997; or Revision 02, dated October 25, 2001, that have accumulated 18,900 or more flight cycles or 35,300 or more flight hours as of the effective date of this AD: Before the accumulation of 24,400 total flight cycles or 45,600 total flight hours, whichever occurs first; or within 120 days after the effective date of this AD; whichever occurs later. New Repair (l) If any crack is detected during any inspection required by paragraph (k) of this AD: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116; or the DGAC (or its delegated agent). No Reporting Requirement (m) Although Airbus Service Bulletin A320–57–1101, Revision 02, dated October 25, 2001; Revision 03, dated July 30, 2003; and Revision 04, dated November 22, 2004; describe procedures for reporting inspection findings to Airbus, this AD does not require such a report. Alternative Methods of Compliance (AMOCs) (n)(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 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. Related Information (o) French airworthiness directive F–2004– 166, dated October 13, 2004, also addresses the subject of this AD. Material Incorporated by Reference (p) You must use the service information specified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE Revision level Airbus service bulletin A320–57–1100, including Appendix 01 ............................................................................................................... A320–57–1100, including Appendices 01 and 02 ............................................................................................... A320–57–1101 ..................................................................................................................................................... A320–57–1101 ..................................................................................................................................................... A320–57–1101 ..................................................................................................................................................... A320–57–1101 ..................................................................................................................................................... sroberts on PROD1PC70 with RULES 1 Original. The optional terminating action specified in paragraph (g) of this AD should be done VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 in accordance with the service bulletins specified in Table 2 of this AD. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\07JNR1.SGM 07JNR1 (1) 03 (1) 02 03 04 Date July 28, 1997. January 16, 2003. July 24, 1997. October 25, 2001. July 30, 2003. November 22, 2004. 32811 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations TABLE 2.—OPTIONAL SERVICE BULLETINS Revision level Airbus service bulletin (1) 03 A320–57–1100, including Appendix 01 ................................................................................................................ A320–57–1100, including Appendices 01 and 02 ................................................................................................ Date July 28, 1997. January 16, 2003. 1 Original. (1) The incorporation by reference of the service information specified in Table 3 of this AD was approved previously by the Director of the Federal Register as of March 8, 2006 (71 FR 8792, February 21, 2006). TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE Revision level Airbus service bulletin A320–57–1100, including Appendix 01 .............................................................................................................. A320–57–1100, including Appendices 01 and 02 .............................................................................................. A320–57–1101 .................................................................................................................................................... A320–57–1101 .................................................................................................................................................... (1) 03 03 04 Date July 28, 1997. January 16, 2003. July 30, 2003. November 22, 2004. 1 Original. (2) The incorporation by reference of Airbus Service Bulletin A320–57–1101, Revision 02, dated October 25, 2001, was approved previously by the Director of the Federal Register as of April 21, 2004 (69 FR 17906, April 6, 2004). (3) The incorporation by reference of Airbus Service Bulletin A320–57–1101, dated July 24, 1997, was approved previously by the Director of the Federal Register as of December 18, 1998 (63 FR 66753, December 3, 1998). (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 26, 2006. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5121 Filed 6–6–06; 8:45 am] sroberts on PROD1PC70 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22628; Directorate Identifier 2005–NM–056–AD; Amendment 39–14631; AD 2006–12–06] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–300, –400, –500, –700, and –800 Series Airplanes; Model 747–400 and –400F Series Airplanes; Model 757–200 Series Airplanes; Model 767– 300 Series Airplanes; and Model 777– 300 Series Airplanes Equipped With Certain Driessen or Showa Galleys or Driessen Closets Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires inspecting to determine if certain galleys and closets are installed, and replacing the spiral wire wrapping of the electrical cables of the galleys and closets with new spiral wire wrapping if necessary. This AD results from testing and reports from the manufacturer indicating unacceptable flammability properties of wire wrapping installed in certain galleys and closets. We are issuing this AD to prevent fire propagation or smoke in the cabin area due to electrical arcing or sparking and ignition of the spiral wire wrapping. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 This AD becomes effective July 12, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 12, 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Robert Kaufman, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6433; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: DATES: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would E:\FR\FM\07JNR1.SGM 07JNR1

Agencies

[Federal Register Volume 71, Number 109 (Wednesday, June 7, 2006)]
[Rules and Regulations]
[Pages 32807-32811]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5121]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24953; Directorate Identifier 2006-NM-084-AD; 
Amendment 39-14628; AD 2006-04-11 R1]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A321-100 Series Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is revising an existing airworthiness directive (AD) 
that applies to certain Airbus Model A321-111, -112, and -131 
airplanes. That AD currently requires repetitive inspections to detect 
fatigue cracking in the area surrounding certain attachment holes of 
the forward pintle fittings of the main landing gear (MLG) and the 
actuating cylinder anchorage fittings on the inner rear spar; and 
repair, if necessary. That AD also provides for optional terminating 
action for the repetitive inspections, adds inspections of three 
additional mounting holes, and revises the thresholds for the currently 
required inspections. We issued that AD to detect and correct fatigue 
cracking on the inner rear spar of the wings, which could result in 
reduced structural integrity of the airplane. This new AD retains the 
requirements and revises the applicability of that AD. This AD results 
from the discovery of a typographical error in the applicability of 
that AD, which could cause the unsafe condition on an affected airplane 
to remain uncorrected. We are issuing this AD to detect and correct 
fatigue cracking on the inner rear spar of the wings, which could 
result in reduced structural integrity of the airplane.

DATES: Effective June 22, 2006.
    The incorporation by reference of the publications specified in the 
following table, as listed in the regulations, was approved previously 
by the Director of the Federal Register as of March 8, 2006 (71 FR 
8792, February 21, 2006).

                   Material Incorporated by Reference
------------------------------------------------------------------------
                                  Revision
    Airbus service bulletin        level                Date
------------------------------------------------------------------------
A320-57-1100, including              (\1\)  July 28, 1997.
 Appendix 01.
A320-57-1100, including                 03  January 16, 2003.
 Appendices 01 and 02.
A320-57-1101...................         03  July 30, 2003.

[[Page 32808]]

 
A320-57-1101...................         04  November 22, 2004.
------------------------------------------------------------------------
\1\ Original.

    The incorporation by reference of Airbus Service Bulletin A320-57-
1101, Revision 02, dated October 25, 2001, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of April 21, 2004 (69 FR 17906, April 6, 2004).
    The incorporation by reference of Airbus Service Bulletin A320-57-
1101, dated July 24, 1997, as listed in the regulations, was approved 
previously by the Director of the Federal Register as of December 18, 
1998 (63 FR 66753, December 3, 1998).
    We must receive comments on this AD by August 7, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
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.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    On February 9, 2006, we issued AD 2006-04-11, amendment 39-14492 
(71 FR 8792, February 21, 2006), for certain Airbus Model A321-111, -
112, and -131 airplanes. That AD requires repetitive inspections to 
detect fatigue cracking in the area surrounding certain attachment 
holes of the forward pintle fittings of the main landing gear (MLG) and 
the actuating cylinder anchorage fittings on the inner rear spar; and 
repair, if necessary. That AD also provides for optional terminating 
action for the repetitive inspections, adds inspections of three 
additional mounting holes, and revises the thresholds for the currently 
required inspections. That AD resulted from manufacturer analysis of 
the fatigue and damage tolerance of the area surrounding certain 
mounting holes of the MLG. We issued that AD to detect and correct 
fatigue cracking on the inner rear spar of the wings, which could 
result in reduced structural integrity of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-04-11, amendment 39-14492, a typographical 
error was discovered in the applicability of that AD, which could cause 
the unsafe condition on an affected airplane to remained uncorrected. 
The applicability of that AD states, ``all manufacturer serial numbers 
(MSN), except MSN 364 and 365.'' The correct reference should have 
been, ``all manufacturer serial numbers (MSN), except MSN 364 and 
385.''

Clarification of No Reporting Requirement

    Airbus Service Bulletin A320-57-1101, Revision 03, dated July 30, 
2003, which also describes procedures for reporting inspection findings 
to Airbus, was inadvertently omitted from paragraph (m) of AD 2006-04-
11, which specifies that we do not require reports of inspection 
findings. We have revised paragraph (m) of this AD to include Service 
Bulletin A320-57-1101, Revision 3.

FAA's Determination and Requirements of this AD

    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    This new AD revises the applicability of AD 2006-04-11 by 
correcting the reference, ``all manufacturer serial numbers (MSN), 
except MSN 364 and 365,'' to read ``all manufacturer serial numbers 
(MSN), except MSN 364 and 385.'' This new AD also retains the 
requirements of AD 2006-04-11.

Costs of Compliance

    The revisions made to this AD add no additional economic burden. 
The current costs for this AD are repeated for the convenience of 
affected operators, as follows:
    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this AD 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
we consider that this AD is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    If an affected airplane is imported and placed on the U.S. Register 
in the future, it would require approximately 22 work hours to 
accomplish the required actions at an average labor rate of $65 per 
work hour. Based on these figures, the cost impact of this AD would be 
$1,430 per airplane.
    If an operator elects to accomplish the optional terminating action 
provided by this AD, it would take approximately 520 work hours to 
accomplish, at an average labor rate of $65 per work hour. The cost of 
required parts would be approximately $17,540 per airplane. Based on 
these figures, the cost impact of the optional terminating action would 
be $51,340 per airplane.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in

[[Page 32809]]

less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to the 
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2006-24953; Directorate Identifier 2006-NM-084-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the AD that 
might suggest a need to modify it.
    We will post all comments we receive, without change, to http://
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 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 
http://dms.dot.gov.

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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

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 the 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 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 39-14492 (71 FR 8792, February 21, 2006), and adding 
the following new airworthiness directive (AD):

AD 2006-04-11 R1 Airbus: Amendment 39-14628. Docket No. FAA-2006-
24953; Directorate Identifier 2006-NM-084-AD.

Effective Date

    (a) This AD becomes effective June 22, 2006.

Affected ADs

    (b) This AD revises AD 2006-04-11.

Applicability

    (c) This AD applies to Airbus Model A321-111, -112, and -131 
airplanes, certificated in any category; all manufacturer serial 
numbers (MSN), except MSN 364 and 385; and except for those 
airplanes that have received Airbus Modification 24977 in 
production.

Unsafe Condition

    (d) This AD results from manufacturer analysis of the fatigue 
and damage tolerance of the area surrounding certain mounting holes 
of the main landing gear (MLG). The FAA is issuing this AD to detect 
and correct fatigue cracking on the inner rear spar of the wings, 
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 Requirements of AD 2004-07-15

Repetitive Inspections and Corrective Actions

    (f) Prior to the accumulation of 20,000 total flight cycles, or 
within 120 days after December 18, 1998 (the effective date of AD 
98-25-05, amendment 39-10928), whichever occurs later, perform an 
ultrasonic inspection to detect fatigue cracking in the area 
surrounding certain attachment holes of the forward pintle fittings 
of the MLG and the actuating cylinder anchorage fittings on the 
inner rear spar, in accordance with Airbus Service Bulletin A320-57-
1101, dated July 24, 1997; or Revision 02, dated October 25, 2001.
    (1) If no cracking is detected, prior to further flight, repair 
the sealant in the inspected areas and repeat the ultrasonic 
inspections thereafter at intervals not to exceed 7,700 flight 
cycles, until paragraph (g), (i), or (k) of this AD is accomplished.
    (2) If any cracking is detected, prior to further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent).

Optional Terminating Action

    (g) Accomplishment of visual and eddy current inspections to 
detect cracking in the area surrounding certain attachment holes of 
the forward pintle fittings of the MLG and the actuating cylinder 
anchorage fittings on the inner rear spar; follow-on corrective 
actions, as applicable; and rework of the attachment holes; in 
accordance with Airbus Service Bulletin A320-57-1100, including 
Appendix 01, dated July 28, 1997; or Revision 03, including 
Appendices 01 and 02, dated January 16, 2003; constitutes 
terminating action for the repetitive inspection requirements of 
this AD. Actions

[[Page 32810]]

accomplished in accordance with Airbus Service Bulletin A320-57-
1100, Revision 01, including Appendices 01 and 02, dated June 4, 
1999; or Revision 02, including Appendices 01 and 02, dated October 
25, 2001; are considered acceptable for compliance with the optional 
terminating action specified in this paragraph. If any cracking is 
detected during accomplishment of any inspection described in the 
service bulletin, and the service bulletin specifies to contact 
Airbus for appropriate action: Prior to further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent).

Repetitive Inspections for Airplanes Not Previously Inspected Per 
Paragraph (f)

    (h) For airplanes on which the initial inspection required by 
paragraph (f) of this AD has not been accomplished as of April 21, 
2004 (the effective date of AD 2004-07-15): Accomplish the 
inspection required by paragraph (f) of this AD, at the earlier of 
the times specified in paragraphs (h)(1) and (h)(2) of this AD. If 
no cracking is found, repeat the inspection thereafter at intervals 
not to exceed 5,500 flight cycles or 10,200 flight hours, whichever 
occurs first, until paragraph (g) or (k) of this AD is accomplished. 
Accomplishment of this paragraph eliminates the need to accomplish 
repetitive inspections at the intervals required by paragraph (f)(1) 
of this AD.
    (1) Prior to the accumulation of 20,000 total flight cycles.
    (2) Prior to the accumulation of 37,300 total flight hours, or 
within 120 days after April 21, 2004, whichever occurs later.

Repetitive Inspections for Airplanes Previously Inspected Per 
Paragraph (f)

    (i) For airplanes on which the initial inspection required by 
paragraph (f) of this AD has been accomplished as of April 21, 2004, 
and no cracking was found: Do the next inspection at the earlier of 
the times specified in paragraphs (i)(1) and (i)(2) of this AD, and 
repeat the inspection thereafter at intervals not to exceed 5,500 
flight cycles or 10,200 flight hours, whichever occurs first, until 
paragraph (g) or (k) of this AD is accomplished. Accomplishment of 
this paragraph terminates the repetitive inspections required by 
paragraph (f)(1) of this AD.
    (1) Within 7,700 flight cycles since the most recent inspection.
    (2) At the later of the times specified in paragraph (i)(2)(i) 
or (i)(2)(ii) of this AD:
    (i) Within 5,500 flight cycles or 10,200 flight hours since the 
most recent inspection, whichever occurs first.
    (ii) Within 120 days after April 21, 2004.

Existing Repair

    (j) If any cracking is detected during any inspection required 
by paragraph (h) or (i) of this AD: Prior to further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent).

New Requirements of This AD

Initial and Repetitive Inspections

    (k) Within the applicable compliance times specified by 
paragraph (k)(1), (k)(2), or (k)(3) of this AD, perform an 
ultrasonic inspection for cracking of the attachment holes of the 
MLG pintle fittings in the inner rear spar in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1101, 
Revision 03, dated July 30, 2003; or Revision 04, dated November 22, 
2004. If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 5,500 flight cycles or 10,200 flight hours, 
whichever occurs first, until paragraph (g) of this AD is 
accomplished. Accomplishment of this paragraph terminates the 
repetitive inspections required by paragraphs (f)(1), (h), and (i) 
of this AD.
    (1) For airplanes that have never been inspected in accordance 
with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or 
Revision 02, dated October 25, 2001: Before the accumulation of 
20,000 total flight cycles or 37,300 total flight hours, whichever 
occurs first; or within 120 days after the effective date of this 
AD; whichever occurs later.
    (2) For airplanes previously inspected in accordance with Airbus 
Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, 
dated October 25, 2001, that have accumulated less than 18,900 total 
flight cycles or 35,300 total flight hours as of the effective date 
of this AD: Within 5,500 flight cycles or 10,200 flight hours, 
whichever occurs first, after the previous inspection performed in 
accordance with Airbus Service Bulletin A320-57-1101, Revision 02, 
dated October 25, 2001; or within 120 days after the effective date 
of this AD; whichever occurs later.
    (3) For airplanes previously inspected in accordance with Airbus 
Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, 
dated October 25, 2001, that have accumulated 18,900 or more flight 
cycles or 35,300 or more flight hours as of the effective date of 
this AD: Before the accumulation of 24,400 total flight cycles or 
45,600 total flight hours, whichever occurs first; or within 120 
days after the effective date of this AD; whichever occurs later.

New Repair

    (l) If any crack is detected during any inspection required by 
paragraph (k) of this AD: Prior to further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116; or the DGAC (or its delegated agent).

No Reporting Requirement

    (m) Although Airbus Service Bulletin A320-57-1101, Revision 02, 
dated October 25, 2001; Revision 03, dated July 30, 2003; and 
Revision 04, dated November 22, 2004; describe procedures for 
reporting inspection findings to Airbus, this AD does not require 
such a report.

Alternative Methods of Compliance (AMOCs)

    (n)(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 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.

Related Information

    (o) French airworthiness directive F-2004-166, dated October 13, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (p) You must use the service information specified in Table 1 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

            Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
                                   Revision
     Airbus service bulletin        level                Date
------------------------------------------------------------------------
A320-57-1100, including Appendix      (\1\)  July 28, 1997.
 01.
A320-57-1100, including                  03  January 16, 2003.
 Appendices 01 and 02.
A320-57-1101....................      (\1\)  July 24, 1997.
A320-57-1101....................         02  October 25, 2001.
A320-57-1101....................         03  July 30, 2003.
A320-57-1101....................         04  November 22, 2004.
------------------------------------------------------------------------
\1\ Original.

    The optional terminating action specified in paragraph (g) of 
this AD should be done in accordance with the service bulletins 
specified in Table 2 of this AD.

[[Page 32811]]



                                      Table 2.--Optional Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                                            Revision
                 Airbus service bulletin                     level                       Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01......................      (\1\)  July 28, 1997.
A320-57-1100, including Appendices 01 and 02.............         03  January 16, 2003.
----------------------------------------------------------------------------------------------------------------
\1\ Original.

    (1) The incorporation by reference of the service information 
specified in Table 3 of this AD was approved previously by the 
Director of the Federal Register as of March 8, 2006 (71 FR 8792, 
February 21, 2006).

                                Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                                                           Revision
                 Airbus service bulletin                    level                        Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01.....................      (\1\)  July 28, 1997.
A320-57-1100, including Appendices 01 and 02............         03  January 16, 2003.
A320-57-1101............................................         03  July 30, 2003.
A320-57-1101............................................         04  November 22, 2004.
----------------------------------------------------------------------------------------------------------------
\1\ Original.

    (2) The incorporation by reference of Airbus Service Bulletin 
A320-57-1101, Revision 02, dated October 25, 2001, was approved 
previously by the Director of the Federal Register as of April 21, 
2004 (69 FR 17906, April 6, 2004).
    (3) The incorporation by reference of Airbus Service Bulletin 
A320-57-1101, dated July 24, 1997, was approved previously by the 
Director of the Federal Register as of December 18, 1998 (63 FR 
66753, December 3, 1998).
    (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 26, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-5121 Filed 6-6-06; 8:45 am]
BILLING CODE 4910-13-P