Airworthiness Directives; Airbus Model A330 Airplanes; and Model A340-200 and -300 Airplanes, 15063-15067 [E7-5908]

Download as PDF Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules § 915.11 District. 6. Add a new § 915.43 to read as follows: (a) District 1 shall include MiamiDade County. (b) District 2 shall include all of the production area except Miami-Dade County. 3. In § 915.22, paragraph (b)(1) is revised to read as follows: § 915.22 § 915.43 Nomination. (a) * * * (b) Successor members. (1) The Committee shall hold or cause to be held a meeting or meetings of growers and handlers in each district to designate nominees for successor members and alternate members of the Committee; or the Committee may conduct nominations in Districts 1 and 2 by mail in a manner recommended by the Committee and approved by the Secretary. Such nominations shall be submitted to the Secretary by the Committee not later than March 1 of each year. The Committee shall prescribe procedural rules, not inconsistent with the provisions of this section, for the conduct of nomination. * * * * * 4. In § 915.30, paragraph (c) is revised to read as follows: § 915.30 Procedure. (a) * * * (b) * * * (c) For any recommendation of the Committee for an assessment rate change, a quorum of seven Committee members and a two-thirds majority vote of approval of those in attendance is required. 5. In § 915.41, paragraph (b) is revised to read as follows: pwalker on PROD1PC71 with PROPOSALS § 915.41 Assessments. (a) * * * (b) The Secretary shall fix the rate of assessment per 55-pounds of fruit or equivalent in any container or in bulk, to be paid by each such handler. At any time during or after a fiscal year, the Secretary may increase the rate of assessment, in order to secure sufficient funds to cover any later finding by the Secretary relative to the expense which may be incurred. Such increase shall be applied to all fruit handled during the applicable fiscal year. In order to provide funds for the administration of the provisions of this part, the Committee may accept the payment of assessments in advance, or borrow money on an emergency short-term basis. The authority of the Committee to borrow money is subject to approval of the Secretary and may be used only to meet financial obligations as the obligations occur or to allow the Committee to adjust its reserve funds to meet such obligations. VerDate Aug<31>2005 17:30 Mar 29, 2007 Jkt 211001 Contributions. The Committee may accept voluntary contributions. Such contributions shall be free from any encumbrances by the donor and the Committee shall retain complete control of their use. 7. Revise § 915.45 to read as follows: § 915.45 Production research, marketing research and development. The committee may, with the approval of the Secretary, establish or provide for the establishment of production research, marketing research and development projects designed to assist, improve or promote the marketing, distribution, and consumption or efficient production of avocados. Such products may provide for any form of marketing promotion, including paid advertising. The expenses of such projects shall be paid from funds collected pursuant to the applicable provisions of § 915.41, or from such other funds as approved by the USDA. Dated: March 23, 2007. Lloyd C. Day, Administrator, Agricultural Marketing Service. [FR Doc. E7–5792 Filed 3–29–07; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket Number FAA–2007–27739; Directorate Identifier 2006–NM–250–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330 Airplanes; and Model A340–200 and –300 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The aim of * * * [Special Federal Aviation Regulation (SFAR) 88] is to require all holders of type certificates * * * to carry out PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 15063 a definition review against explosion hazards. The unsafe condition is the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by April 30, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • 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. • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. Examining the AD Docket You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5227) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register E:\FR\FM\30MRP1.SGM 30MRP1 15064 Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket Number FAA–2007–27739; Directorate Identifier 2006–NM–250–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 we receive about this proposed AD. Discussion pwalker on PROD1PC71 with PROPOSALS The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued Airworthiness Directive 2006–0322, dated October 18, 2006 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 88). By mail referenced 04/00/02/07/01–L296 of March 4th, 2002 and 04/00/02/07/03–L024 of February 3rd, 2003 the JAA (Joint Aviation Authorities) recommended to the National Aviation Authorities (NAA) the application of a similar regulation. The aim of this regulation is to require all holders of type certificates for passenger transport aircraft certified after January 1st, 1958 with a capacity of 30 passengers or more, or a payload of 3402 kg or more, to carry out a definition review against explosion hazards. Consequently, the following measures are rendered mandatory: • [inspection and] replacement [if necessary] of the white P-clips by blue Pclips which are more fuel resistant [to] remove the risks of fuel quantity indicator (FQI) and fuel level sensor system (FLSS) VerDate Aug<31>2005 17:30 Mar 29, 2007 Jkt 211001 harnesses chafing against the metallic part of the P-clip, • Modification of electrical bonding of equipment installed in fuel tanks in order to re-establish the conformity with the design definition by introducing additional bonding leads, electrical bonding points and electrical bonding of a support bracket for a diffuser assembly installed between Rib 1 and Rib 2 on the stringers of the Number 1 bottom skin panel, • Modification of bonding points, installation of additional bonding leads and other modifications of the Additional Center Tank (ACT), • Modification to increase the distance between metallic parts on the THS (trimmable horizontal stabilizer) Trim Tank, • Installation of a bonding lead between the bonding tags on the Jettison valve actuator and drive assembly. You may obtain further information by examining the MCAI in the AD docket. The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation Number 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. The Joint Aviation Authorities (JAA) has issued a regulation that is similar to SFAR 88. (The JAA is an associated body of the European Civil Aviation Conference (ECAC) representing the civil aviation regulatory authorities of a number of European States who have agreed to co-operate in developing and implementing common safety regulatory standards and procedures.) Under this regulation, the JAA stated that all members of the ECAC that hold type certificates for transport category airplanes are required to conduct a design review against explosion risks. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Relevant Service Information Airbus has issued the following service bulletins: • A330–28–3082, including Appendix 01, Revision 02, dated August 11, 2006. • A330–28–3092, including Appendix 01, Revision 01, dated December 14, 2005. • A330–28–3101, Revision 01, dated October 11, 2006. • A330–55–3016, Revision 1, dated February 12, 1997. • A340–28–4073, Revision 01, October 9, 1998. • A340–28–4078, dated March 17, 2000. • A340–28–4097, including Appendix 01, Revision 02, dated August 16, 2006. • A340–28–4107, including Appendix 01, Revision 01, dated December 14, 2005. • A340–28–4118, Revision 01, dated October 11, 2006. • A340–55–4017, Revision 1, dated February 12, 1997. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another E:\FR\FM\30MRP1.SGM 30MRP1 Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. pwalker on PROD1PC71 with PROPOSALS Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 28 products of U.S. registry. We also estimate that it would take about 600 work-hours per product to comply with this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $2,718 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,420,104, or $50,718 per product. 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 VerDate Aug<31>2005 17:30 Mar 29, 2007 Jkt 211001 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 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 this 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. 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 FAA amends § 39.13 by adding the following new AD: Airbus: Docket Number FAA–2007–27739; Directorate Identifier 2006-NM–250–AD. Comments Due Date (a) We must receive comments by April 30, 2007. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A330, A340–200, and A340–300 airplanes, PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 15065 all certified models, all serial numbers, certificated in any category. Subject (d) Fuel. Reason (e) The mandatory continuing airworthiness information (MCAI) states: [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 88). By mail referenced 04/00/02/07/01–L296 of March 4th, 2002 and 04/00/02/07/03–L024 of February 3rd, 2003 the JAA (Joint Aviation Authorities) recommended to the National Aviation Authorities (NAA) the application of a similar regulation. The aim of this regulation is to require all holders of type certificates for passenger transport aircraft certified after January 1st, 1958 with a capacity of 30 passengers or more, or a payload of 3402 kg or more, to carry out a definition review against explosion hazards. Consequently, the following measures are rendered mandatory: • [Inspection and ] replacement [if necessary] of the white P-clips by blue Pclips which are more fuel resistant [to] remove the risks of fuel quantity indicator (FQI) and fuel level sensor system (FLSS) harnesses chafing against the metallic part of the P-clip, • Modification of electrical bonding of equipment installed in fuel tanks in order to re-establish the conformity with the design definition by introducing additional bonding leads, electrical bonding points and electrical bonding of a support bracket for a diffuser assembly installed between Rib 1 and Rib 2 on the stringers of the Number 1 bottom skin panel, • Modification of bonding points, installation of additional bonding leads and other modifications of the Additional Center Tank (ACT), • Modification to increase the distance between metallic parts on the THS (trimmable horizontal stabilizer) Trim Tank, • Installation of a bonding lead between the bonding tags on the Jettison valve actuator and drive assembly. Actions and Compliance (f) Within 38 months after the effective date of this AD, unless already done, do the actions in paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(5). (1) Action number 1, applicable to Model A330, A340–200, and A340–330 aircraft, all certified models, all serial numbers, except for airplanes on which Airbus Modification 47634 has been embodied in production: Perform a detailed visual inspection of the Pclips in the wings and center fuel tanks, and apply the applicable corrective actions, in accordance with the instructions of Airbus Service Bulletin A330–28–3092, Revision 01, dated December 14, 2005; or Airbus Service Bulletin A340–28–4107, Revision 01, dated December 14, 2005. (2) Action number 2, applicable to Model A330, A340–200, and A340–300 airplanes, all certified models, all serial numbers, except for airplanes on which Airbus Modifications 49135 and 49630 and 51825 and 55118 have been embodied in E:\FR\FM\30MRP1.SGM 30MRP1 15066 Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules production or modified in-service in accordance with both Airbus Service Bulletin A330–28–3082, including Appendix 01, and Airbus Service Bulletin A330–28–3101, or both Airbus Service Bulletin A340–28–4097 and Airbus Service Bulletin A340–28–4118: Modify the electrical bonding of the equipment installed in fuel tanks, in accordance with both Airbus Service Bulletin A330–28–3082, Revision 02, dated August 11, 2006, and Airbus Service Bulletin A330– 28–3101, Revision 01, dated October 11, 2006; or both Airbus Service Bulletin A340– 28–4097, including Appendix 01, Revision 02, dated August 16, 2006, and Airbus Service Bulletin A340–28–4118, Revision 01, dated October 11, 2006; as applicable. (3) Action number 3, applicable to Model A340–200 and A340–300 airplanes, all certified models, all serial numbers, which have Airbus modification 42612/Airbus Service Bulletin A340–28–4047 or Airbus modification 44002/Airbus Service Bulletin A340–28–4066 or Airbus modification 44005/Airbus Service Bulletin A340–28– 4067 embodied in production/in-service (installation of an ACT (Additional Center Tank)), except airplanes modified by Airbus Service Bulletin A340–28–4078 in-service: Modify the electrical bonding in the ACT in accordance with the instructions of Airbus Service Bulletin A340–28–4078, dated March 17, 2000. (4) Action number 4, applicable to Model A330–300 airplanes, –301, –321, –322, –341, –342 models, all serial numbers except for airplanes on which Airbus Modification 44252 has been embodied in production or modified in-service in accordance with Airbus Service Bulletin A330–55–3016; and Model A340–200 and Model A340–300 airplanes, all certified models, all serial numbers, except for airplanes on which Airbus Modification 44252 has been embodied in production or modified inservice in accordance with Airbus Service Bulletin A340–55–4017: Increase the distance between metallic parts on the THS (trimmable horizontal stabilizer) trim tank in accordance with the instructions of Airbus Service Bulletin A330–55–3016, Revision 1, dated February 12, 1997; or Airbus Service Bulletin A340–55–4017, Revision 1, dated February 12, 1997; as applicable. (5) Action number 5, applicable to Model A340–200 and A340–300 airplanes, all certified models, all serial numbers, except for airplanes which have Airbus modification 46142 embodied in production or modified in-service in accordance with Airbus Service Bulletin A340–28–4073, Revision 01, dated October 9, 1998: Install a bonding lead between the bonding tags on the Jettison valve actuator and drive assembly in accordance with the instructions of Airbus Service Bulletin A340–28–4073, Revision 01, dated October 9, 1998. (6) Actions done before the effective date of this AD in accordance with the service bulletins listed in Table 1 of this AD are acceptable for compliance with the corresponding requirements of paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(5) of this AD, as applicable. TABLE 1.—CREDIT SERVICE BULLETINS Airbus Service Bulletin A330–28–3082 A330–28–3082 A330–28–3101 A330–55–3016 A340–28–4073 A340–28–4097 A340–28–4097 A340–28–4118 A340–55–4017 Revision level ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ ........................................................................ FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, ANM–116, International Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tim Backman, Aerospace Engineer; 1601 Lind Ave. SW., Date Original ................................................................................... 01 ........................................................................................... Original ................................................................................... Original ................................................................................... Original ................................................................................... Original ................................................................................... 01 ........................................................................................... Original ................................................................................... Original ................................................................................... Renton, Washington 98057–3356, telephone (425) 227–2797; fax (425) 227–1149. To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated June 14, 2004. March 2, 2005. June 5, 2006. August 20, 1996. May 14, 1998. June 14, 2004. March 3, 2005. June 5, 2006. August 20, 1996. agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2006–0322, dated October 18, 2006, and the service bulletins in Table 2 of this AD, for related information. TABLE 2.—RELATED SERVICE BULLETINS Revision level Date A330–28–3082, including Appendix 01 .................................. A330–28–3092 ........................................................................ pwalker on PROD1PC71 with PROPOSALS Airbus Service Bulletin 02 ........................................................................................... 01 ........................................................................................... A330–28–3101 ........................................................................ A330–55–3016 ........................................................................ A340–28–4073 ........................................................................ A340–28–4078 ........................................................................ A340–28–4097, including Appendix 01 .................................. A340–28–4107 ........................................................................ 01 ........................................................................................... 1 ............................................................................................. 01 ........................................................................................... Original ................................................................................... 02 ........................................................................................... 01 ........................................................................................... A340–28–4118 ........................................................................ A340–55–4017 ........................................................................ 01 ........................................................................................... 1 ............................................................................................. August 11, 2006. December 14, 2005. October 11, 2006. February 12, 1997. October 9, 1998. March 17, 2000. August 16, 2006. December 14, 2005. October 11, 2006. February 12, 1997. VerDate Aug<31>2005 17:30 Mar 29, 2007 Jkt 211001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\30MRP1.SGM 30MRP1 Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules Issued in Renton, Washington, on March 23, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–5908 Filed 3–29–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27741; Directorate Identifier 2006–NM–261–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 Airplanes; and Model A340–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). pwalker on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as keel beam rupture, which affects the structural integrity of the area. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by April 30, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • 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. • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. VerDate Aug<31>2005 17:30 Mar 29, 2007 Jkt 211001 Examining the AD Docket You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5227) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–27741; Directorate Identifier 2006–NM–261–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because 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 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 15067 post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2006–0315, dated October 13, 2006 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states that during the A330 and A340 aircraft fatigue test, cracks appeared on the right and left sides between the crossing area of the keel beam fitting and the front spar on the center wing box (CWB). This situation if not corrected can lead in the worst case to keel beam rupture, which affects the structural integrity of the area. In order to maintain the structural integrity of the aircraft, the MCAI requires a repetitive special detailed inspection on the horizontal flange of the keel beam in the area of the first fastener hole aft of FR (frame) 40, follow-up actions (further inspections, installation of new fasteners, and sealing the fasteners), and repair if necessary. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletin A330–57–3081, including Appendix 01, Revision 02, dated January 24, 2006; and Service Bulletin A340–57–4089, including Appendix 01, Revision 02, dated January 24, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. The compliance times for doing the actions described in the service bulletins are as follows: • Service Bulletin A330–57–3081: The mandatory thresholds range from the earlier of 19,100 flight cycles or 57,300 flight hours, to the earlier of 24,200 flight cycles or 72,800 flight hours; the repetitive intervals range from the earlier of 9,800 flight cycles or 29,400 flight hours, to the earlier of 13,500 flight cycles or 40,500 flight hours. • Service Bulletin A340–57–4089: The mandatory thresholds range from the earlier of 19,000 flight cycles or 95,000 flight hours, to the earlier of 24,600 flight cycles or 49,200 flight hours; the repetitive intervals range from the earlier of 9,200 flight cycles or 46,000 flight hours, to the earlier of 12,600 flight cycles or 63,000 flight hours. E:\FR\FM\30MRP1.SGM 30MRP1

Agencies

[Federal Register Volume 72, Number 61 (Friday, March 30, 2007)]
[Proposed Rules]
[Pages 15063-15067]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-5908]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket Number FAA-2007-27739; Directorate Identifier 2006-NM-250-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 Airplanes; and Model 
A340-200 and -300 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    The aim of * * * [Special Federal Aviation Regulation (SFAR) 88] 
is to require all holders of type certificates * * * to carry out a 
definition review against explosion hazards.

The unsafe condition is the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane. The 
proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by April 30, 2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Fax: (202) 493-2251.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     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.
     Federal eRulemaking Portal: http://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
dms.dot.gov; or in person at the Docket Management Facility between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Office (telephone (800) 647-5227) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register

[[Page 15064]]

requirements. We also continue to meet our technical decision-making 
responsibilities to identify and correct unsafe conditions on U.S.-
certificated products.
    This proposed AD references the MCAI and related service 
information that we considered in forming the engineering basis to 
correct the unsafe condition. The proposed AD contains text copied from 
the MCAI and for this reason might not follow our plain language 
principles.

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket Number FAA-2007-
27739; Directorate Identifier 2006-NM-250-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued 
Airworthiness Directive 2006-0322, dated October 18, 2006 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 
88).
    By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and 
04/00/02/07/03-L024 of February 3rd, 2003 the JAA (Joint Aviation 
Authorities) recommended to the National Aviation Authorities (NAA) 
the application of a similar regulation.
    The aim of this regulation is to require all holders of type 
certificates for passenger transport aircraft certified after 
January 1st, 1958 with a capacity of 30 passengers or more, or a 
payload of 3402 kg or more, to carry out a definition review against 
explosion hazards.
    Consequently, the following measures are rendered mandatory:
     [inspection and] replacement [if necessary] of the 
white P-clips by blue P-clips which are more fuel resistant [to] 
remove the risks of fuel quantity indicator (FQI) and fuel level 
sensor system (FLSS) harnesses chafing against the metallic part of 
the P-clip,
     Modification of electrical bonding of equipment 
installed in fuel tanks in order to re-establish the conformity with 
the design definition by introducing additional bonding leads, 
electrical bonding points and electrical bonding of a support 
bracket for a diffuser assembly installed between Rib 1 and Rib 2 on 
the stringers of the Number 1 bottom skin panel,
     Modification of bonding points, installation of 
additional bonding leads and other modifications of the Additional 
Center Tank (ACT),
     Modification to increase the distance between metallic 
parts on the THS (trimmable horizontal stabilizer) Trim Tank,
     Installation of a bonding lead between the bonding tags 
on the Jettison valve actuator and drive assembly.

You may obtain further information by examining the MCAI in the AD 
docket.
    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation Number 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: Single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    The Joint Aviation Authorities (JAA) has issued a regulation that 
is similar to SFAR 88. (The JAA is an associated body of the European 
Civil Aviation Conference (ECAC) representing the civil aviation 
regulatory authorities of a number of European States who have agreed 
to co-operate in developing and implementing common safety regulatory 
standards and procedures.) Under this regulation, the JAA stated that 
all members of the ECAC that hold type certificates for transport 
category airplanes are required to conduct a design review against 
explosion risks.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.

Relevant Service Information

    Airbus has issued the following service bulletins:
     A330-28-3082, including Appendix 01, Revision 02, dated 
August 11, 2006.
     A330-28-3092, including Appendix 01, Revision 01, dated 
December 14, 2005.
     A330-28-3101, Revision 01, dated October 11, 2006.
     A330-55-3016, Revision 1, dated February 12, 1997.
     A340-28-4073, Revision 01, October 9, 1998.
     A340-28-4078, dated March 17, 2000.
     A340-28-4097, including Appendix 01, Revision 02, dated 
August 16, 2006.
     A340-28-4107, including Appendix 01, Revision 01, dated 
December 14, 2005.
     A340-28-4118, Revision 01, dated October 11, 2006.
     A340-55-4017, Revision 1, dated February 12, 1997.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another

[[Page 15065]]

country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 28 products of U.S. registry. We also estimate that 
it would take about 600 work-hours per product to comply with this 
proposed AD. The average labor rate is $80 per work-hour. Required 
parts would cost about $2,718 per product. Where the service 
information lists required parts costs that are covered under warranty, 
we have assumed that there will be no charge for these costs. As we do 
not control warranty coverage for affected parties, some parties may 
incur costs higher than estimated here. Based on these figures, we 
estimate the cost of the proposed AD on U.S. operators to be 
$1,420,104, or $50,718 per product.

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 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 this 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.

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 FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket Number FAA-2007-27739; Directorate Identifier 2006-
NM-250-AD.

Comments Due Date

    (a) We must receive comments by April 30, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A330, A340-200, and 
A340-300 airplanes, all certified models, all serial numbers, 
certificated in any category.

Subject

    (d) Fuel.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 
88).
    By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and 
04/00/02/07/03-L024 of February 3rd, 2003 the JAA (Joint Aviation 
Authorities) recommended to the National Aviation Authorities (NAA) 
the application of a similar regulation.
    The aim of this regulation is to require all holders of type 
certificates for passenger transport aircraft certified after 
January 1st, 1958 with a capacity of 30 passengers or more, or a 
payload of 3402 kg or more, to carry out a definition review against 
explosion hazards.
    Consequently, the following measures are rendered mandatory:
     [Inspection and ] replacement [if necessary] of the 
white P-clips by blue P-clips which are more fuel resistant [to] 
remove the risks of fuel quantity indicator (FQI) and fuel level 
sensor system (FLSS) harnesses chafing against the metallic part of 
the P-clip,
     Modification of electrical bonding of equipment 
installed in fuel tanks in order to re-establish the conformity with 
the design definition by introducing additional bonding leads, 
electrical bonding points and electrical bonding of a support 
bracket for a diffuser assembly installed between Rib 1 and Rib 2 on 
the stringers of the Number 1 bottom skin panel,
     Modification of bonding points, installation of 
additional bonding leads and other modifications of the Additional 
Center Tank (ACT),
     Modification to increase the distance between metallic 
parts on the THS (trimmable horizontal stabilizer) Trim Tank,
     Installation of a bonding lead between the bonding tags 
on the Jettison valve actuator and drive assembly.

Actions and Compliance

    (f) Within 38 months after the effective date of this AD, unless 
already done, do the actions in paragraphs (f)(1), (f)(2), (f)(3), 
(f)(4), and (f)(5).
    (1) Action number 1, applicable to Model A330, A340-200, and 
A340-330 aircraft, all certified models, all serial numbers, except 
for airplanes on which Airbus Modification 47634 has been embodied 
in production: Perform a detailed visual inspection of the P-clips 
in the wings and center fuel tanks, and apply the applicable 
corrective actions, in accordance with the instructions of Airbus 
Service Bulletin A330-28-3092, Revision 01, dated December 14, 2005; 
or Airbus Service Bulletin A340-28-4107, Revision 01, dated December 
14, 2005.
    (2) Action number 2, applicable to Model A330, A340-200, and 
A340-300 airplanes, all certified models, all serial numbers, except 
for airplanes on which Airbus Modifications 49135 and 49630 and 
51825 and 55118 have been embodied in

[[Page 15066]]

production or modified in-service in accordance with both Airbus 
Service Bulletin A330-28-3082, including Appendix 01, and Airbus 
Service Bulletin A330-28-3101, or both Airbus Service Bulletin A340-
28-4097 and Airbus Service Bulletin A340-28-4118: Modify the 
electrical bonding of the equipment installed in fuel tanks, in 
accordance with both Airbus Service Bulletin A330-28-3082, Revision 
02, dated August 11, 2006, and Airbus Service Bulletin A330-28-3101, 
Revision 01, dated October 11, 2006; or both Airbus Service Bulletin 
A340-28-4097, including Appendix 01, Revision 02, dated August 16, 
2006, and Airbus Service Bulletin A340-28-4118, Revision 01, dated 
October 11, 2006; as applicable.
    (3) Action number 3, applicable to Model A340-200 and A340-300 
airplanes, all certified models, all serial numbers, which have 
Airbus modification 42612/Airbus Service Bulletin A340-28-4047 or 
Airbus modification 44002/Airbus Service Bulletin A340-28-4066 or 
Airbus modification 44005/Airbus Service Bulletin A340-28-4067 
embodied in production/in-service (installation of an ACT 
(Additional Center Tank)), except airplanes modified by Airbus 
Service Bulletin A340-28-4078 in-service: Modify the electrical 
bonding in the ACT in accordance with the instructions of Airbus 
Service Bulletin A340-28-4078, dated March 17, 2000.
    (4) Action number 4, applicable to Model A330-300 airplanes, -
301, -321, -322, -341, -342 models, all serial numbers except for 
airplanes on which Airbus Modification 44252 has been embodied in 
production or modified in-service in accordance with Airbus Service 
Bulletin A330-55-3016; and Model A340-200 and Model A340-300 
airplanes, all certified models, all serial numbers, except for 
airplanes on which Airbus Modification 44252 has been embodied in 
production or modified in-service in accordance with Airbus Service 
Bulletin A340-55-4017: Increase the distance between metallic parts 
on the THS (trimmable horizontal stabilizer) trim tank in accordance 
with the instructions of Airbus Service Bulletin A330-55-3016, 
Revision 1, dated February 12, 1997; or Airbus Service Bulletin 
A340-55-4017, Revision 1, dated February 12, 1997; as applicable.
    (5) Action number 5, applicable to Model A340-200 and A340-300 
airplanes, all certified models, all serial numbers, except for 
airplanes which have Airbus modification 46142 embodied in 
production or modified in-service in accordance with Airbus Service 
Bulletin A340-28-4073, Revision 01, dated October 9, 1998: Install a 
bonding lead between the bonding tags on the Jettison valve actuator 
and drive assembly in accordance with the instructions of Airbus 
Service Bulletin A340-28-4073, Revision 01, dated October 9, 1998.
    (6) Actions done before the effective date of this AD in 
accordance with the service bulletins listed in Table 1 of this AD 
are acceptable for compliance with the corresponding requirements of 
paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(5) of this AD, as 
applicable.

                   Table 1.--Credit Service Bulletins
------------------------------------------------------------------------
   Airbus Service Bulletin      Revision level            Date
------------------------------------------------------------------------
A330-28-3082.................  Original.......  June 14, 2004.
A330-28-3082.................  01.............  March 2, 2005.
A330-28-3101.................  Original.......  June 5, 2006.
A330-55-3016.................  Original.......  August 20, 1996.
A340-28-4073.................  Original.......  May 14, 1998.
A340-28-4097.................  Original.......  June 14, 2004.
A340-28-4097.................  01.............  March 3, 2005.
A340-28-4118.................  Original.......  June 5, 2006.
A340-55-4017.................  Original.......  August 20, 1996.
------------------------------------------------------------------------

FAA AD Differences

    Note: This AD differs from the MCAI and/ or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: Tim 
Backman, Aerospace Engineer; 1601 Lind Ave. SW., Renton, Washington 
98057-3356, telephone (425) 227-2797; fax (425) 227-1149. To request 
a different method of compliance or a different compliance time for 
this AD, follow the procedures in 14 CFR 39.19. Before using any 
approved AMOC on any airplane to which the AMOC applies, notify your 
appropriate principal inspector (PI) in the FAA Flight Standards 
District Office (FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2006-0322, dated October 18, 2006, and the 
service bulletins in Table 2 of this AD, for related information.

                   Table 2.--Related Service Bulletins
------------------------------------------------------------------------
   Airbus Service Bulletin      Revision level            Date
------------------------------------------------------------------------
A330-28-3082, including        02.............  August 11, 2006.
 Appendix 01.
A330-28-3092.................  01.............  December 14, 2005.
A330-28-3101.................  01.............  October 11, 2006.
A330-55-3016.................  1..............  February 12, 1997.
A340-28-4073.................  01.............  October 9, 1998.
A340-28-4078.................  Original.......  March 17, 2000.
A340-28-4097, including        02.............  August 16, 2006.
 Appendix 01.
A340-28-4107.................  01.............  December 14, 2005.
A340-28-4118.................  01.............  October 11, 2006.
A340-55-4017.................  1..............  February 12, 1997.
------------------------------------------------------------------------



[[Page 15067]]

    Issued in Renton, Washington, on March 23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-5908 Filed 3-29-07; 8:45 am]
BILLING CODE 4910-13-P