Airworthiness Directives; Airbus Model A300 B2 Series Airplanes, Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model A310-300 Series Airplanes, and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 53739-53743 [05-17980]

Download as PDF Federal Register / Vol. 70, No. 175 / Monday, September 12, 2005 / Proposed Rules satisfactory level ($14,303). The assessment rate of $0.95 per hundredweight of assessable dates was then determined by applying the following formula where: A = 2004–05 reserve on 10/1/05 ($1,000). B = 2005–06 reserve on 9/30/06 ($14,303). C = 2005–06 expenses ($169,197). D = Cull Surplus Fund ($2,000). E = 2005–06 expected shipments (190,000 hundredweight). (B ¥ A + C ¥ D) E ÷ $0.95 per hundredweight. Estimated shipments should provide $180,500 in assessment income. Income derived from handler assessments and $2,000 from the cull surplus fund would be adequate to cover budgeted expenses. Funds in the administrative reserve are expected to total about $14,303 by September 30, 2006, and therefore would be less than the maximum permitted by the order (not to exceed 50 percent of the average of expenses incurred during the most recent five preceding crop years as required under § 987.72(c)). A review of historical information and preliminary information pertaining to the upcoming crop year indicates that the grower price for the 2005–06 season could range between $45 and $50 per hundredweight of dates. Therefore, the estimated assessment revenue for the 2005–06 crop year as a percentage of total grower revenue is approximately 2 percent. This action would increase the assessment obligation imposed on handlers under the Federal marketing order. While assessments impose some additional costs on handlers, the costs are minimal and uniform on all handlers. Some of the additional costs may be passed on to producers. However, these costs would be offset by the benefits derived by the operation of the marketing order. In addition, the committee’s meeting was widely publicized throughout the California date industry and all interested persons were invited to attend the meeting and participate in committee deliberations on all issues. Like all committee meetings, the June 16, 2005, meeting was a public meeting and all entities, both large and small, were able to express views on this issue. Finally, interested persons are invited to submit information on the regulatory and informational impacts of this action on small businesses. This proposed rule would impose no additional reporting or recordkeeping requirements on either small or large California date handlers. As with all Federal marketing order programs, reports and forms are periodically VerDate Aug<18>2005 15:21 Sep 09, 2005 Jkt 205001 reviewed to reduce information requirements and duplication by industry and public sector agencies. USDA has not identified any relevant Federal rules that duplicate, overlap, or conflict with this rule. A small business guide on complying with fruit, vegetable, and specialty crop marketing agreements and orders may be viewed at: http://www.ams.usda.gov/ fv/moab.html. Any questions about the compliance guide should be sent to Jay Guerber at the previously mentioned address in the FOR FURTHER INFORMATION CONTACT section. A 30-day comment period is provided to allow interested persons to respond to this proposed rule. Thirty days is deemed appropriate because: (1) The 2005–06 crop year begins on October 1, 2005, and the marketing order requires that the rate of assessment for each crop year apply to all assessable dates handled during such crop year; (2) the committee needs to have sufficient funds to pay its expenses which are incurred on a continuous basis; and (3) handlers are aware of this action which was unanimously recommended by the committee at a public meeting and is similar to other assessment rate actions issued in past years. List of Subjects in 7 CFR Part 987 Dates, Marketing agreements, Reporting and recordkeeping requirements. For the reasons set forth in the preamble, 7 CFR part 987 is proposed to be amended as follows: PART 987—DOMESTIC DATES PRODUCED OR PACKED IN RIVERSIDE COUNTY, CALIFORNIA 1. The authority citation for 7 CFR part 987 continues to read as follows: Authority: 7 U.S.C. 601–674. 2. Section 987.339 is revised to read as follows: § 987.339 Assessment rate. On and after October 1, 2005, an assessment rate of $0.95 per hundredweight is established for California dates. Dated: September 6, 2005. Lloyd C. Day, Administrator, Agricultural Marketing Service. [FR Doc. 05–17963 Filed 9–9–05; 8:45 am] BILLING CODE 3410–02–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 53739 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22384; Directorate Identifier 2005–NM–131–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 Series Airplanes, Model A300 B4 Series Airplanes, Model A310–200 Series Airplanes, Model A310–300 Series Airplanes, and Model 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: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus transport category airplanes. This proposed AD would require repetitive eddy current inspections for cracks of the stiffener fittings of the fuselage at frame (FR) 12A, and corrective actions if necessary. This proposed AD also provides a terminating action for the inspections. This proposed AD results from reports of cracks on the upper attachment fitting of the stiffener fitting at FR12A. We are proposing this AD to prevent failure of the stiffener fittings, which could result in the reduced structural integrity of the floor and rods around FR12A. DATES: We must receive comments on this proposed AD by October 12, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed 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 Jacques Leborgne, Airbus Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac E:\FR\FM\12SEP1.SGM 12SEP1 53740 Federal Register / Vol. 70, No. 175 / Monday, September 12, 2005 / Proposed Rules Cedex, France, fax (+33) 5 61 93 36 14, for service information identified in this proposed AD for Model A300 B2 series airplanes and Model A300 B4 series airplanes. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD for Model A310–200 series airplanes, Model A310–300 series airplanes, and Model A300–600 series airplanes. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Include the docket number ‘‘FAA–2005–22384; Directorate Identifier 2005–NM–131– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. 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 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 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. VerDate Aug<18>2005 15:21 Sep 09, 2005 Jkt 205001 Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A300 B2 and A300 B4 series airplanes, Model A310–200 and –300 series airplanes, and Model A300–600 series airplanes. The DGAC advises that there are reports of cracks on the upper attachment fitting of the stiffener fitting on the floor beam at frame (FR) 12A, right-hand and left-hand sides of the fuselage. The DGAC states that the cracks are due to a combined effect of the pressurization of the cabin and bending induced by thermal effects which generates a longitudinal force in the floor beam, causing a high level of fatigue in the fitting. This condition, if not corrected, could result in failure of the stiffener fittings, and consequent reduced structural integrity of the floor and rods around FR12A. Relevant Service Information Airbus has issued Service Bulletin A300–53–0365, Revision 01 (for Model A300 B2 and A300 B4 series airplanes); Service Bulletin A300–53–6138, Revision 01 (for Model A300–600 series airplanes); and Service Bulletin A310– 53–2117, Revision 01 (for Model A310– 200 and A310–300 series airplane); all dated April 4, 2005. The service bulletins describe procedures for repetitive eddy current inspections for cracks of the stiffener fittings of the fuselage at FR12A, and corrective action if necessary. Doing the corrective action eliminates the need for the repetitive inspection. The corrective action includes replacing the existing fitting on FR12A with a FR12A crossbeam and installing a new web between FR12A and FR13 at stringer 26. The service bulletins refer to Airbus Service Bulletin A300–53–0364, Revision 02, dated September 24, 2004 (for Model A300 B2 and B4 series airplanes); Service Bulletin A300–53– 6137, Revision 03, dated April 4, 2005 (for Model A300–600 series airplanes); and Service Bulletin A310–53–2116, Revision 02, dated September 24, 2004 (for Model A310–200 and –300 series airplane); as the appropriate sources of service information for doing the corrective action. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F–2005–084, dated May 25, 2005, to ensure the PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are 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 airplanes of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and Service Bulletins.’’ Differences Between the Proposed AD and Service Bulletins Unlike the procedures described in Airbus Service Bulletins A300–53–0365, Revision 01; A300–53–6138, Revision 01; and A310–53–2117, Revision 01; this proposed AD would not permit further flight if cracks are detected in the stiffener fittings of the fuselage at FR12A. We have determined that, because of the safety implications and consequences associated with that cracking, any cracked fitting must be replaced before further flight. The service bulletins specify to contact the manufacturer for fastener requirements if stiffener fitting FR12A has been replaced, but this proposed AD would require contacting the FAA or the DGAC (or its delegated agent). 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, requirements that we or the DGAC approve would be acceptable for compliance with this proposed AD. Operators should note that, although the Accomplishment Instructions of the referenced service bulletins describe procedures for reporting results, this proposed AD would not require those actions. We do not need this information from operators. E:\FR\FM\12SEP1.SGM 12SEP1 Federal Register / Vol. 70, No. 175 / Monday, September 12, 2005 / Proposed Rules Difference Between French Airworthiness Directive and This Proposed AD The applicability of French airworthiness directive F–2005–084, dated May 25, 2005, excludes airplanes that accomplished Airbus Service Bulletin A300–53–0364, dated December 1, 2003; Revision 01, dated May 5, 2004; or Revision 02, dated September 24, 2004; or Airbus Service Bulletin A300–53–6137, dated December 1, 2003; Revision 01, dated May 5, 2004; Revision 02, dated September 24, 2004; or Revision 03, dated April 4, 2005; or Airbus Service Bulletin A310–53–2116, dated December 1, 2003; Revision 01, dated May 5, 2004; or Revision 02, dated September 24, 2004; in service. However, we have not excluded those airplanes in the applicability of this proposed AD; rather, this proposed AD includes a requirement to accomplish the actions specified in the latest revision of the service bulletins, as applicable. This requirement would ensure that the actions specified in the service bulletins and required by this proposed AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this proposed AD unless an alternative method of compliance is approved. Costs of Compliance This proposed AD would affect about 202 airplanes of U.S. registry. The proposed inspection would take between 57 and 64 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed inspection for U.S. operators is between $748,410 and $840,320, or between $3,705 and $4,160 per airplane, per inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that VerDate Aug<18>2005 15:21 Sep 09, 2005 Jkt 205001 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 proposed 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, Safety. 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 53741 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–22384; Directorate Identifier 2005–NM–131–AD. Comments Due Date (a) The FAA must receive comments on this AD action by October 12, 2005. Affected ADs (b) None. Applicability: (c) This AD applies to Airbus Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes; Model A300 B4–2C, B4– 103, and B4–203 airplanes; Model A300 B4– 601, B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4–622R airplanes; Model A300 F4–605R and F4– 622R airplanes; Model A300 C4–605R Variant F airplanes; Model A310–203, –204, –221, and –222 airplanes; and Model A310– 304, –322, –324, and –325 airplanes; certificated in any category; except for airplanes on which AIRBUS Modification 12662 has been done in production. Unsafe Condition (d) This AD results from reports of cracks on the upper attachment fitting of the stiffener fitting at frame (FR) 12A. We are issuing this AD to prevent failure of the stiffener fittings, which could result in the reduced structural integrity of the floor and rods around FR12A. 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. Inspections (f) At the applicable initial inspection threshold specified in Table 1 of this AD or within the applicable grace period specified in Table 2 of this AD, whichever occurs later: Do an eddy current inspection for cracks of the stiffener fittings of the fuselage at FR12A, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–0365, Revision 01 (for Model A300 B2– 1A, B2–1C, B2K–3C, and B2–203 airplanes, and Model A300 B4–2C, B4–103, and B4–203 airplanes); Service Bulletin A300–53–6138, Revision 01 (for Model A300 B4–601, B4– 603, B4–620, and B4–622 airplanes, Model A300 B4–605R and B4–622R airplanes, Model A300 F4–605R and F4–622R airplanes, and Model A300 C4–605R Variant F airplanes); or Service Bulletin A310–53– 2117, Revision 01 (for Model A310–203, –204, –221, and –222 airplanes, and Model A310–304, –322, –324, and –325 airplanes); all dated April 4, 2005; as applicable. Repeat the inspection thereafter at intervals not to exceed the applicable compliance time specified in Table 1 of this AD until the actions specified in paragraph (h) of this AD are done. E:\FR\FM\12SEP1.SGM 12SEP1 53742 Federal Register / Vol. 70, No. 175 / Monday, September 12, 2005 / Proposed Rules TABLE 1.—COMPLIANCE TIMES FOR INITIAL AND REPETITIVE INSPECTIONS Do the initial inspection prior to the accumulation of— For airplanes identified as— Configuration 4, 2005. Configuration 4, 2005. Configuration 4, 2005. Configuration 4, 2005. Configuration 4, 2005. Configuration 4, 2005. Configuration 4, 2005. Configuration 4, 2005. Configuration 4, 2005. And repeat at intervals not to exceed— 01 in Airbus Service Bulletin A300–53–0365, Revision 01, dated April 19,300 total flight cycles ........ 11,450 flight cycles. 02 in Airbus Service Bulletin A300–53–0365, Revision 01, dated April 15,500 total flight cycles ........ 9,200 flight cycles. 01 in Airbus Service Bulletin A300–53–6138, Revision 01, dated April 19,300 total flight cycles ........ 11,450 flight cycles. 02 in Airbus Service Bulletin A300–53–6138, Revision 01, dated April 17,600 total flight cycles ........ 11,450 flight cycles. 03 in Airbus Service Bulletin A300–53–6138, Revision 01, dated April 12,700 total flight cycles ........ 8,000 flight cycles. 04 in Airbus Service Bulletin A300–53–6138, Revision 01, dated April 10,200 total flight cycles ........ 6,400 flight cycles. 01 in Airbus Service Bulletin A310–53–2117, Revision 01, dated April 19,300 total flight cycles ........ 11,450 flight cycles. 02 in Airbus Service Bulletin A310–53–2117, Revision 01, dated April 17,600 total flight cycles ........ 11,450 flight cycles. 03 in Airbus Service Bulletin A310–53–2117, Revision 01, dated April 12,700 total flight cycles ........ 8,000 flight cycles. TABLE 2.—GRACE PERIOD FOR THE INITIAL INSPECTION For Airbus model— Grace period is— A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes ........................... A300 B4–2C, B4–103, and B4–203 airplanes; A300 B4–601, B4–603, B4–620, and B4–622 airplanes; A300 B4–605R and B4–622R airplanes; A300 F4–605R and F4–622R airplanes; A300 C4–605R Variant F airplanes; A310–203, –204, –221, and –222 airplanes; and A310–304, –322, –324, and –325 airplanes. Corrective Action (g) If any cracking is found during any inspection required by paragraph (f) of this AD, before further flight, do the replacement and installation specified in paragraph (h) of this AD. Terminating Action (h) Replacing the existing fitting on FR12A with a FR12A crossbeam and installing a new web between FR12A and FR13 at stringer 26 in accordance with Airbus Service Bulletin A300–53–0364, Revision 02, dated September 24, 2004 (for Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes, and Model A300 B4–2C, B4–103, and B4–203 Within 2,500 flight cycles after the effective date of this AD. Within 2,000 flight cycles after the effective date of this AD. airplanes); Service Bulletin A300–53–6137, Revision 03, dated April 4, 2005 (for Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes, Model A300 B4–605R and B4– 622R airplanes, Model A300 F4–605R and F4–622R airplanes, and Model A300 C4– 605R Variant F airplanes); or Service Bulletin A310–53–2116, Revision 02, dated September 24, 2004 (for Model A310–203, –204, –221, and –222 airplanes, and Model A310–304, –322, –324, and –325 airplanes); as applicable; and except as required by paragraph (i) of this AD; constitutes terminating action for the requirements of this AD. (i) Where the service bulletins specify to contact the manufacturer for certain information, before further flight, do the terminating action according to a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent). Actions Accomplished According to Previous Issue of Service Bulletin (j) Actions accomplished before the effective date of this AD according to the Airbus service bulletins specified in Table 3 of this AD are considered acceptable for compliance with the corresponding actions specified in this AD. TABLE 3.—PREVIOUS ISSUES OF SERVICE BULLETINS Airbus Service Bulletin A300–53–0364 A300–53–0364 A300–53–0365 A300–53–6137 A300–53–6137 A300–53–6137 A300–53–6138 A310–53–2116 A310–53–2116 A310–53–2117 VerDate Aug<18>2005 Revision level .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. .................................................................................................................................. 15:21 Sep 09, 2005 Jkt 205001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Original .................. 01 ........................... Original .................. Original .................. 01 ........................... 02 ........................... Original .................. Original .................. 01 ........................... Original .................. E:\FR\FM\12SEP1.SGM 12SEP1 Date December 1, 2003. May 5, 2004. December 1, 2003. December 1, 2003. May 5, 2004. September 24, 2004. December 1, 2003. December 1, 2003. May 5, 2004. December 1, 2003. Federal Register / Vol. 70, No. 175 / Monday, September 12, 2005 / Proposed Rules No Reporting Required (k) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (l) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (m) French airworthiness directive F– 2005–084, dated May 25, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on August 24, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–17980 Filed 9–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22383; Directorate Identifier 2005–NM–102–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100B SUD, 747–200B, 747– 300, 747–400, and 747–400D Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 747–100B SUD, 747–300, 747–400, and 747–400D series airplanes; and Model 747–200B series airplanes having a stretched upper deck. This proposed AD would require repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220, and related investigative and corrective actions if necessary. This proposed AD results from new reports of severed tension ties, as well as numerous reports of cracked tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. We are proposing this AD VerDate Aug<18>2005 15:21 Sep 09, 2005 Jkt 205001 to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by October 27, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Include the docket number ‘‘FAA–2005–22383; Directorate Identifier 2005–NM–102– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. 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 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, PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 53743 business, labor union, etc.). You may review 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. Discussion We previously issued AD 2005–05– 08, amendment 39–13997 (70 FR 12113, March 11, 2005). That AD applies to certain Boeing Model 747–100B SUD, –300, –400, and –400D series airplanes. That AD requires a one-time inspection for discrepancies of the fuselage frame to tension tie joints at body stations (BS) 1120 through 1220, and to determine if steel splice plates are installed on the fuselage frames, and related investigative and corrective actions. That AD was prompted by reports of severed tension ties found at the fuselage frame joints at BS 1120 and 1140. These severed tension ties resulted from fatigue cracking due to an incorrect configuration (installation of aluminum splice plates instead of steel splice plates during the manufacturing process). Since we issued AD 2005–05–08, we have received additional reports of severed tension ties. While these severed tension ties were also attributed to fatigue, the tension ties in these cases were properly configured according to the applicable Boeing Engineering Drawings. We have also received numerous reports of fatigue cracking of tension ties, as well as broken fasteners and cracks in the frame and shear ties adjacent to tension ties for the upper deck between BS 1120 and 1220. Also, we have received reports of cracking in the shear web between the BS 1120 and BS 1140 tension ties. Cracking of the tension ties, shear webs, and frames of the upper deck; if not corrected; could result in rapid decompression of the airplane. Certain Boeing 747–200B series airplanes have been modified under a certain Boeing-owned supplemental type certificate to include a stretched upper deck (SUD). These airplanes E:\FR\FM\12SEP1.SGM 12SEP1

Agencies

[Federal Register Volume 70, Number 175 (Monday, September 12, 2005)]
[Proposed Rules]
[Pages 53739-53743]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-17980]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22384; Directorate Identifier 2005-NM-131-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 Series Airplanes, 
Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model 
A310-300 Series Airplanes, and Model 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: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus transport category airplanes. This proposed AD would 
require repetitive eddy current inspections for cracks of the stiffener 
fittings of the fuselage at frame (FR) 12A, and corrective actions if 
necessary. This proposed AD also provides a terminating action for the 
inspections. This proposed AD results from reports of cracks on the 
upper attachment fitting of the stiffener fitting at FR12A. We are 
proposing this AD to prevent failure of the stiffener fittings, which 
could result in the reduced structural integrity of the floor and rods 
around FR12A.

DATES: We must receive comments on this proposed AD by October 12, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed 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 Jacques Leborgne, Airbus Customer Service Directorate, 1 
Rond Point Maurice Bellonte, 31707 Blagnac

[[Page 53740]]

Cedex, France, fax (+33) 5 61 93 36 14, for service information 
identified in this proposed AD for Model A300 B2 series airplanes and 
Model A300 B4 series airplanes. Contact Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France, for service information 
identified in this proposed AD for Model A310-200 series airplanes, 
Model A310-300 series airplanes, and Model A300-600 series airplanes.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Include the docket number ``FAA-
2005-22384; Directorate Identifier 2005-NM-131-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    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 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 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.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified us that an unsafe 
condition may exist on certain Airbus Model A300 B2 and A300 B4 series 
airplanes, Model A310-200 and -300 series airplanes, and Model A300-600 
series airplanes.
    The DGAC advises that there are reports of cracks on the upper 
attachment fitting of the stiffener fitting on the floor beam at frame 
(FR) 12A, right-hand and left-hand sides of the fuselage. The DGAC 
states that the cracks are due to a combined effect of the 
pressurization of the cabin and bending induced by thermal effects 
which generates a longitudinal force in the floor beam, causing a high 
level of fatigue in the fitting. This condition, if not corrected, 
could result in failure of the stiffener fittings, and consequent 
reduced structural integrity of the floor and rods around FR12A.

Relevant Service Information

    Airbus has issued Service Bulletin A300-53-0365, Revision 01 (for 
Model A300 B2 and A300 B4 series airplanes); Service Bulletin A300-53-
6138, Revision 01 (for Model A300-600 series airplanes); and Service 
Bulletin A310-53-2117, Revision 01 (for Model A310-200 and A310-300 
series airplane); all dated April 4, 2005. The service bulletins 
describe procedures for repetitive eddy current inspections for cracks 
of the stiffener fittings of the fuselage at FR12A, and corrective 
action if necessary. Doing the corrective action eliminates the need 
for the repetitive inspection. The corrective action includes replacing 
the existing fitting on FR12A with a FR12A crossbeam and installing a 
new web between FR12A and FR13 at stringer 26.
    The service bulletins refer to Airbus Service Bulletin A300-53-
0364, Revision 02, dated September 24, 2004 (for Model A300 B2 and B4 
series airplanes); Service Bulletin A300-53-6137, Revision 03, dated 
April 4, 2005 (for Model A300-600 series airplanes); and Service 
Bulletin A310-53-2116, Revision 02, dated September 24, 2004 (for Model 
A310-200 and -300 series airplane); as the appropriate sources of 
service information for doing the corrective action.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directive F-
2005-084, dated May 25, 2005, to ensure the continued airworthiness of 
these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are 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 airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
the Proposed AD and Service Bulletins.''

Differences Between the Proposed AD and Service Bulletins

    Unlike the procedures described in Airbus Service Bulletins A300-
53-0365, Revision 01; A300-53-6138, Revision 01; and A310-53-2117, 
Revision 01; this proposed AD would not permit further flight if cracks 
are detected in the stiffener fittings of the fuselage at FR12A. We 
have determined that, because of the safety implications and 
consequences associated with that cracking, any cracked fitting must be 
replaced before further flight.
    The service bulletins specify to contact the manufacturer for 
fastener requirements if stiffener fitting FR12A has been replaced, but 
this proposed AD would require contacting the FAA or the DGAC (or its 
delegated agent). 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, requirements that we or the DGAC approve would be acceptable for 
compliance with this proposed AD.
    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletins describe procedures 
for reporting results, this proposed AD would not require those 
actions. We do not need this information from operators.

[[Page 53741]]

Difference Between French Airworthiness Directive and This Proposed AD

    The applicability of French airworthiness directive F-2005-084, 
dated May 25, 2005, excludes airplanes that accomplished Airbus Service 
Bulletin A300-53-0364, dated December 1, 2003; Revision 01, dated May 
5, 2004; or Revision 02, dated September 24, 2004; or Airbus Service 
Bulletin A300-53-6137, dated December 1, 2003; Revision 01, dated May 
5, 2004; Revision 02, dated September 24, 2004; or Revision 03, dated 
April 4, 2005; or Airbus Service Bulletin A310-53-2116, dated December 
1, 2003; Revision 01, dated May 5, 2004; or Revision 02, dated 
September 24, 2004; in service. However, we have not excluded those 
airplanes in the applicability of this proposed AD; rather, this 
proposed AD includes a requirement to accomplish the actions specified 
in the latest revision of the service bulletins, as applicable. This 
requirement would ensure that the actions specified in the service 
bulletins and required by this proposed AD are accomplished on all 
affected airplanes. Operators must continue to operate the airplane in 
the configuration required by this proposed AD unless an alternative 
method of compliance is approved.

Costs of Compliance

    This proposed AD would affect about 202 airplanes of U.S. registry. 
The proposed inspection would take between 57 and 64 work hours per 
airplane, at an average labor rate of $65 per work hour. Based on these 
figures, the estimated cost of the proposed inspection for U.S. 
operators is between $748,410 and $840,320, or between $3,705 and 
$4,160 per airplane, per inspection cycle.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this 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 proposed 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, Safety.

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-2005-22384; Directorate Identifier 2005-NM-
131-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October 
12, 2005.

Affected ADs

    (b) None.
    Applicability: (c) This AD applies to Airbus Model A300 B2-1A, 
B2-1C, B2K-3C, and B2-203 airplanes; Model A300 B4-2C, B4-103, and 
B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R and F4-622R airplanes; Model A300 C4-605R Variant F airplanes; 
Model A310-203, -204, -221, and -222 airplanes; and Model A310-304, 
-322, -324, and -325 airplanes; certificated in any category; except 
for airplanes on which AIRBUS Modification 12662 has been done in 
production.

Unsafe Condition

    (d) This AD results from reports of cracks on the upper 
attachment fitting of the stiffener fitting at frame (FR) 12A. We 
are issuing this AD to prevent failure of the stiffener fittings, 
which could result in the reduced structural integrity of the floor 
and rods around FR12A.
    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.

Inspections

    (f) At the applicable initial inspection threshold specified in 
Table 1 of this AD or within the applicable grace period specified 
in Table 2 of this AD, whichever occurs later: Do an eddy current 
inspection for cracks of the stiffener fittings of the fuselage at 
FR12A, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-53-0365, Revision 01 (for Model A300 B2-1A, 
B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, 
and B4-203 airplanes); Service Bulletin A300-53-6138, Revision 01 
(for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model 
A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R 
airplanes, and Model A300 C4-605R Variant F airplanes); or Service 
Bulletin A310-53-2117, Revision 01 (for Model A310-203, -204, -221, 
and -222 airplanes, and Model A310-304, -322, -324, and -325 
airplanes); all dated April 4, 2005; as applicable.
    Repeat the inspection thereafter at intervals not to exceed the 
applicable compliance time specified in Table 1 of this AD until the 
actions specified in paragraph (h) of this AD are done.

[[Page 53742]]



                        Table 1.--Compliance Times for Initial and Repetitive Inspections
----------------------------------------------------------------------------------------------------------------
                                     Do the initial inspection prior to the     And repeat at intervals not to
  For airplanes identified as--                accumulation of--                           exceed--
----------------------------------------------------------------------------------------------------------------
Configuration 01 in Airbus         19,300 total flight cycles...............  11,450 flight cycles.
 Service Bulletin A300-53-0365,
 Revision 01, dated April 4, 2005.
Configuration 02 in Airbus         15,500 total flight cycles...............  9,200 flight cycles.
 Service Bulletin A300-53-0365,
 Revision 01, dated April 4, 2005.
Configuration 01 in Airbus         19,300 total flight cycles...............  11,450 flight cycles.
 Service Bulletin A300-53-6138,
 Revision 01, dated April 4, 2005.
Configuration 02 in Airbus         17,600 total flight cycles...............  11,450 flight cycles.
 Service Bulletin A300-53-6138,
 Revision 01, dated April 4, 2005.
Configuration 03 in Airbus         12,700 total flight cycles...............  8,000 flight cycles.
 Service Bulletin A300-53-6138,
 Revision 01, dated April 4, 2005.
Configuration 04 in Airbus         10,200 total flight cycles...............  6,400 flight cycles.
 Service Bulletin A300-53-6138,
 Revision 01, dated April 4, 2005.
Configuration 01 in Airbus         19,300 total flight cycles...............  11,450 flight cycles.
 Service Bulletin A310-53-2117,
 Revision 01, dated April 4, 2005.
Configuration 02 in Airbus         17,600 total flight cycles...............  11,450 flight cycles.
 Service Bulletin A310-53-2117,
 Revision 01, dated April 4, 2005.
Configuration 03 in Airbus         12,700 total flight cycles...............  8,000 flight cycles.
 Service Bulletin A310-53-2117,
 Revision 01, dated April 4, 2005.
----------------------------------------------------------------------------------------------------------------


            Table 2.--Grace Period for the Initial Inspection
------------------------------------------------------------------------
           For Airbus model--                   Grace period is--
------------------------------------------------------------------------
A300 B2-1A, B2-1C, B2K-3C, and B2-203    Within 2,500 flight cycles
 airplanes.                               after the effective date of
                                          this AD.
A300 B4-2C, B4-103, and B4-203           Within 2,000 flight cycles
 airplanes; A300 B4-601, B4-603, B4-      after the effective date of
 620, and B4-622 airplanes; A300 B4-      this AD.
 605R and B4-622R airplanes; A300 F4-
 605R and F4-622R airplanes; A300 C4-
 605R Variant F airplanes; A310-203, -
 204, -221, and -222 airplanes; and
 A310-304, -322, -324, and -325
 airplanes.
------------------------------------------------------------------------

Corrective Action

    (g) If any cracking is found during any inspection required by 
paragraph (f) of this AD, before further flight, do the replacement 
and installation specified in paragraph (h) of this AD.

Terminating Action

    (h) Replacing the existing fitting on FR12A with a FR12A 
crossbeam and installing a new web between FR12A and FR13 at 
stringer 26 in accordance with Airbus Service Bulletin A300-53-0364, 
Revision 02, dated September 24, 2004 (for Model A300 B2-1A, B2-1C, 
B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-
203 airplanes); Service Bulletin A300-53-6137, Revision 03, dated 
April 4, 2005 (for Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes); or Service Bulletin A310-53-2116, Revision 02, dated 
September 24, 2004 (for Model A310-203, -204, -221, and -222 
airplanes, and Model A310-304, -322, -324, and -325 airplanes); as 
applicable; and except as required by paragraph (i) of this AD; 
constitutes terminating action for the requirements of this AD.
    (i) Where the service bulletins specify to contact the 
manufacturer for certain information, before further flight, do the 
terminating action according to a method approved by either the 
Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate; or the DGAC (or its delegated agent).

Actions Accomplished According to Previous Issue of Service Bulletin

    (j) Actions accomplished before the effective date of this AD 
according to the Airbus service bulletins specified in Table 3 of 
this AD are considered acceptable for compliance with the 
corresponding actions specified in this AD.

                                 Table 3.--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus Service Bulletin                   Revision level                            Date
----------------------------------------------------------------------------------------------------------------
A300-53-0364..........................  Original.........................  December 1, 2003.
A300-53-0364..........................  01...............................  May 5, 2004.
A300-53-0365..........................  Original.........................  December 1, 2003.
A300-53-6137..........................  Original.........................  December 1, 2003.
A300-53-6137..........................  01...............................  May 5, 2004.
A300-53-6137..........................  02...............................  September 24, 2004.
A300-53-6138..........................  Original.........................  December 1, 2003.
A310-53-2116..........................  Original.........................  December 1, 2003.
A310-53-2116..........................  01...............................  May 5, 2004.
A310-53-2117..........................  Original.........................  December 1, 2003.
----------------------------------------------------------------------------------------------------------------


[[Page 53743]]

No Reporting Required

    (k) Although the service bulletins referenced in this AD specify to 
submit certain information to the manufacturer, this AD does not 
include that requirement.

Alternative Methods of Compliance (AMOCs)

    (l) The Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.

Related Information

    (m) French airworthiness directive F-2005-084, dated May 25, 2005, 
also addresses the subject of this AD.

    Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-17980 Filed 9-9-05; 8:45 am]
BILLING CODE 4910-13-P