Airworthiness Directives; Airbus Model A310-203 and -222 Airplanes and Model A300 B4-620 Airplanes, 49805-49809 [E9-23094]

Download as PDF Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations FAA AD Differences 2009–20–04 Glaser-Dirks Flugzeugbau Gmbh: Amendment 39–16027; Docket No. FAA–2009–0881; Directorate Identifier 2009–CE–050–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 19, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Model DG–100 gliders, serial numbers 5 and 21 through 103, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 27: Flight Controls. Reason (e) The mandatory continuing airworthiness information (MCAI) states: The Elevator control bearing stand RU19 was required to be inspected for correct production in 1978 in accordance with Technical Note (TN) No. 301/6. In 2009, an accident occurred with a DG–100. The suspension bolt was found torn out of the bearing stand making the elevator uncontrollable. The investigation confirmed that the bearing stand had not been produced correctly. It is therefore assumed that the inspections per TN 301/6 did not produce reliable results. As a consequence, this new Airworthiness Directive (AD) mandates replacement of the bearing stand with a reinforced version. CPrice-Sewell on DSKGBLS3C1PROD with RULES Actions and Compliance (f) Unless already done, do the following actions. (1) Before further flight after October 19, 2009 (the effective date of this AD), inspect the bearing stand RU19 following paragraph 1 of the Instructions section of DG Flugzeugbau Technical note No. 301/26, Rev. 1, dated August 4, 2009. You may take credit for this paragraph if the bearing stand was inspected before October 19, 2009 (the effective date of this AD) following DG Flugzeugbau Technical note No. 301/26, dated July 16, 2009. (2) If any discrepancy is found (crack, delamination, etc.), before further flight replace the bearing stand RU19 following paragraph 3 of the Instructions section of DG Flugzeugbau Technical note No. 301/26, Rev. 1, dated August 4, 2009. (3) Within 3 months after October 19, 2009 (the effective date of this AD) replace the bearing stand RU19 following paragraph 3 of the Instructions section of DG Flugzeugbau Technical note No. 301/26, Rev. 1, dated August 4, 2009. You may take credit for this paragraph if the bearing stand RU19 has been replaced before October 19, 2009 (the effective date of this AD) following DG Flugzeugbau Technical note No. 301/6, dated May 29, 1978, or following paragraph 3 of the Instructions section of DG Flugzeugbau Technical note No. 301/26, dated July 16, 2009. VerDate Nov<24>2008 15:02 Sep 28, 2009 Jkt 217001 Note: This AD differs from the MCAI and/ or service information as follows: (1) DG Flugzeugbau GmbH Technical Note No. 301/26, Rev. 1, dated August 4, 2009, states that instruction 1 may be executed by the pilot/owner. By FAA regulations, this AD requires all affected gliders to have the required actions done by an appropriately rated mechanic. (2) The MCAI states to do the actions following DG Flugzeugbau GmbH Technical Note No. 301/26, dated July 16, 2009. DG Flugzeugbau GmbH updated the technical note after the MCAI was issued. We are requiring you use the updated technical note (DG Flugzeugbau GmbH Technical Note No. 301/26, Rev. 1, dated August 4, 2009) to do the actions of this AD, unless the AD specifies otherwise. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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: Greg Davison, Glider Program Manager, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329–4090. 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 (44 U.S.C. 3501 et.seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. 49805 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact DG Flugzeugbau GmbH, Otto-Lilienthal-Weg 2, 76646 Bruchsal, Federal Republic of Germany; telephone: + 49 (0) 7251 3020140; Fax: +49 (0) 7251 3020149; Internet: http://www.dgflugzeugbau.de/index-e.html; E-Mail: dirks@dg-flugzeugbau.de. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_ locations.html. Issued in Kansas City, Missouri, on September 17, 2009. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–23047 Filed 9–28–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0431; Directorate Identifier 2007–NM–174–AD; Amendment 39–16029; AD 2009–20–06] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310–203 and –222 Airplanes and Model A300 B4–620 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Emergency AD No.: 2009–0163–E, dated July 29, 2009, DG Flugzeugbau GmbH Technical Note No. 301/ 26, dated July 16, 2009; DG Flugzeugbau GmbH Technical Note No. 301/26, Rev. 1, dated August 4, 2009; and DG Flugzeugbau Technical note No. 301/6, dated May 29, 1978, for related information. SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. This 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: Material Incorporated by Reference (i) You must use DG Flugzeugbau GmbH Technical Note No. 301/26, Rev. 1, dated August 4, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 86–102–74(B) [which corresponds to FAA AD 88–06–03, amendment 39–5871] was issued to prevent development of damage, which was discovered during [a] fatigue test in the attachment angles of the rear pressure bulkhead (fuselage frame 80/82). PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\29SER1.SGM 29SER1 49806 Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations Following the life extension activities linked to the A310 program, the interval of inspection for A310–200 aircraft series was reduced from 12000 flight cycles (FC) to 9000 FC * * *. Some stress analysis conducted in the frame of the life extension activities of the A300–600 program leads the manufacturer to reduce as well the interval of inspection applicable to A300B4–620 and A300C4–620 aircraft models. * * * * * The unsafe condition is cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 3, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 3, 2009. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: CPrice-Sewell on DSKGBLS3C1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on May 7, 2009 (74 FR 21274), and proposed to supersede AD 88–06– 03, Amendment 39–5871 (53 FR 7730, March 10, 1988). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 86–102–74(B) [which corresponds to FAA AD 88–06–03] was issued to prevent development of damage, which was discovered during [a] fatigue test in the attachment angles of the rear pressure bulkhead (fuselage frame 80/82). Following the life extension activities linked to the A310 program, the interval of inspection for A310–200 aircraft series was reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the issuance of EASA AD 2007–0157, superseding DGAC France AD 86–102–74(B). Some stress analysis conducted in the frame of the life extension activities of the VerDate Nov<24>2008 15:02 Sep 28, 2009 Jkt 217001 A300–600 program leads the manufacturer to reduce as well the interval of inspection applicable to A300B4–620 and A300C4–620 aircraft models. EASA AD 2007–0297 superseded EASA AD 2007–0157, retaining for A310 aircraft the requirements of EASA AD 2007–0157 and requiring the application of Airbus Service Bulletin (SB) A300–53–6005 Revision 4 on Airbus A300–600 aircraft, reducing the inspection interval from 12000 FC to 9000 FC. [EASA] AD [2007–0297] has been revised to remove an inappropriate reference regarding the normal inspection program from the Compliance section, Note 3. The unsafe condition is cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. The required actions include a modification of the rear pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82, and, for certain airplanes, repetitive inspections for cracks in the rear pressure bulkhead and repair if necessary. The modification includes installing additional attachment angles on the circumference of FR 80/82; installing a filler; installing additional supports between the aft pressure bulkhead and FR 80/82; installing an additional frame stiffener and support between the aft pressure bulkhead and FR 79 at stringer (STGR) 13; modifying the aft lavatories; applying surface protection to the modified area of the aft pressure bulkhead; modifying, reidentifying, and installing the heat and sound insulation in the area of STGR 9 and STGR 13 and between FR 79 and FR 80/82, left and right; and for certain airplanes, doing related investigative and corrective actions if necessary. The related investigative action is doing a visual inspection around the entire circumference between FR 80/82 and the aft pressure bulkhead for damaged filler. The corrective action is removing any damaged filler and the adjacent area around the damage. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Revise Paragraph (f)(4) of the NPRM Airbus requests that we revise paragraph (f)(4) of the NPRM. Airbus states that for the airplanes identified in paragraph (f)(4) of the NPRM, it is not necessary to do the actions in accordance with the service bulletins specified in paragraph (f)(4) of the PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 NPRM. Airbus further states that those airplanes are affected by Airworthiness Limitation Item (ALI) Task 531919–01– 1A, as specified in the service bulletins identified in paragraph (f)(4) of this AD and the MCAI. We agree with the commenter. The actions specified in paragraph (f)(4) of the NPRM are not required for the airplanes identified in that paragraph because those airplanes are already inspected in accordance with ALI Task 531919–01–1A, and no additional actions are necessary. We have confirmed with EASA that this is the intent of the MCAI. We have removed paragraph (f)(4) of the NPRM as it is unnecessary, and added a new Note 1 to this AD to clarify that no action is required by this AD for the airplanes discussed in this paragraph. We have reidentified the subsequent paragraphs accordingly. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect about 32 products of U.S. registry. We also estimate that it will take about 668 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts will cost about $15,322 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 E:\FR\FM\29SER1.SGM 29SER1 Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $2,200,384, or $68,762 per product. section. Comments will be available in the AD docket shortly after receipt. 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. CPrice-Sewell on DSKGBLS3C1PROD with RULES Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES VerDate Nov<24>2008 15:02 Sep 28, 2009 Jkt 217001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ 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] 49807 EASA AD 2007–0297 superseded EASA AD 2007–0157, retaining for A310 aircraft the requirements of EASA AD 2007–0157 and requiring the application of Airbus Service Bulletin (SB) A300–53–6005 Revision 4 on Airbus A300–600 aircraft, reducing the inspection interval from 12000 FC to 9000 FC. [EASA] AD [2007–0297] has been revised to remove an inappropriate reference regarding the normal inspection program from the Compliance section, Note 3. The unsafe condition is cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. The required actions include a modification of the rear pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82; applicable related investigative and corrective actions; and, for certain airplanes, repetitive inspections for cracks in the rear pressure bulkhead and repair if necessary. 2. The FAA amends § 39.13 by removing Amendment 39–5871 (53 FR 7730, March 10, 1988) and adding the following new AD: Requirements of This AD: Actions and Compliance (f) Unless already done, do the following actions. 2009–20–06 Airbus: Amendment 39–16029. Docket No. FAA–2009–0431; Directorate Identifier 2007–NM–174–AD. Modification (1) Except as required by paragraph (f)(2) of this AD: Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later, modify the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame 80/82 and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6006, Revision 3, dated March 24, 1989; or Airbus Mandatory Service Bulletin A310–53–2025, Revision 06, dated August 3, 2006; as applicable. Do all applicable related investigative and corrective actions before further flight. (2) For airplanes identified in paragraph (c) of AD 2006–22–03, amendment 39–14800: At the earlier of the compliance times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions specified in paragraph (f)(1) of this AD. (i) Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (ii) At the compliance time specified in paragraph (h) of AD 2006–22–03. ■ Effective Date (a) This airworthiness directive (AD) becomes effective November 3, 2009. Affected ADs (b) This AD supersedes AD 88–06–03, Amendment 39–5871. Applicability (c) This AD applies to Airbus Model A310– 203 and –222 airplanes, and Model A300 B4– 620 airplanes; certificated in any category; all serial numbers except airplanes on which Airbus Modification 05526 has been incorporated in production. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: ´ ´ DGAC (Direction Generale de l’Aviation Civile) France AD 86–102–74(B) [which corresponds to FAA AD 88–06–03, amendment 39–5871] was issued to prevent development of damage, which was discovered during [a] fatigue test in the attachment angles of the rear pressure bulkhead (fuselage frame 80/82). Following the life extension activities linked to the A310 program, the interval of inspection for A310–200 aircraft series was reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the issuance of EASA AD 2007–0157, superseding DGAC France AD 86–102–74(B). Some stress analysis conducted in the frame of the life extension activities of the A300–600 program leads the manufacturer to reduce as well the interval of inspection applicable to A300B4–620 and A300C4–620 aircraft models. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 Inspections and Corrective Action (3) For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done after the accumulation of 6,000 total flight cycles since first flight: At the times specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an eddy current inspection for any cracking in the critical area of the rear pressure bulkhead between stringers 8 and 18, and repair all cracking before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–6005, Revision 04, dated July 18, 2007; or Airbus Mandatory Service Bulletin A310–53–2024, Revision 05, dated October 13, 2006; as applicable. E:\FR\FM\29SER1.SGM 29SER1 49808 Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations (i) Before or concurrently with the modification required by paragraph (f)(1) or (f)(2) of this AD, as applicable; and (ii) Before the accumulation of 18,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 9,000 flight cycles. Note 1: For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done at or before the accumulation of 6,000 total flight cycles since first flight: No action is required by this AD. For these airplanes, refer to Airbus A300–600 ALI Task 531919–01–1A or Airbus A310 ALI Task 531919–01–1A, as applicable, for guidance on the normal inspection program. (4) Modifications done before the effective date of this AD in accordance with the service bulletins identified in Table 1 of this AD are acceptable for compliance with the requirements of paragraph (f)(1) and (f)(2) of this AD. TABLE 1—MODIFICATIONS DONE USING PREVIOUS SERVICE BULLETINS Model— Airbus Service Bulletin— Revision— Dated— A300 B4–620 airplanes .................................... A300–53–6006 A300–53–6006 A300–53–6006 A310–53–2025 A310–53–2025 A310–53–2025 A310–53–2025 A310–53–2025 A310–53–2025 Original ...................... 1 ................................ 2 ................................ Original ...................... 1 ................................ 2 ................................ 3 ................................ 4 ................................ 5 ................................ May 6, 1986. September 19, 1986. August 11, 1988. April 21, 1986. September 19, 1986. February 16, 1987. April 7, 1987. October 20, 1987. March 24, 1989. A310–203 and –222 airplanes ......................... (5) Inspections done before the effective date of this AD in accordance with the service bulletins identified in Table 2 of this ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. AD are acceptable for compliance with the requirements of paragraph (f)(3) of this AD. TABLE 2—INSPECTIONS DONE WITH PREVIOUS SERVICE BULLETINS Model— Airbus Service Bulletin— Revision— A300 B4–620 airplanes .................................... A300–53–6005 A300–53–6005 A300–53–6005 A300–53–6005 A310–53–2024 A310–53–2024 A310–53–2024 A310–53–2024 A310–53–2024 Original ...................... 1 ................................ 2 ................................ 3 ................................ Original ...................... 1 ................................ 2 ................................ 3 ................................ 4 ................................ A310–203 and –222 airplanes ......................... (6) Modification of the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82 in accordance with paragraph (h) of AD 2006– 22–03 is acceptable for compliance with the corresponding requirement of paragraphs (f)(1) and (f)(2) of this AD. CPrice-Sewell on DSKGBLS3C1PROD with RULES FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows. This AD includes a compliance time specified in paragraph (f)(2) of this AD for airplanes that are also affected by AD 2006–22–03. We realize that the requirements of this AD will necessitate that some operators do the modification required by paragraph (h) of AD 2006–22–03 early. However, accomplishing the modification within the compliance time specified in this AD is required to address cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. ................................................. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. Dated— May 6, 1986. June 20, 1986. September 22, 1986. April 22, 1987. April 21, 1986. June 20, 1986. October 2, 1986. February 17, 1987. February 2, 1988. (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 EASA Airworthiness Directive 2007–0297R1, dated September 17, 2008, and the service bulletins listed in Table 3 of this AD, for related information. TABLE 3—RELATED SERVICE BULLETINS Airbus Service Bulletin Revision Airbus Mandatory Service Bulletin A300–53–6005 ..................................................................................... Airbus Mandatory Service Bulletin A310–53–2024 ..................................................................................... Airbus Mandatory Service Bulletin A310–53–2025 ..................................................................................... VerDate Nov<24>2008 15:02 Sep 28, 2009 Jkt 217001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\29SER1.SGM Date 04 05 06 29SER1 July 18, 2007. October 13, 2006. August 3, 2006. 49809 Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations TABLE 3—RELATED SERVICE BULLETINS—Continued Airbus Service Bulletin Revision Airbus Service Bulletin A300–53–6006 ....................................................................................................... Material Incorporated by Reference (i) You must use the service information contained in Table 4 of this AD to do the Date 3 March 24, 1989. actions required by this AD, unless the AD specifies otherwise. TABLE 4—MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin Airbus Airbus Airbus Airbus Revision Mandatory Service Bulletin A300–53–6005 ..................................................................................... Mandatory Service Bulletin A310–53–2024 ..................................................................................... Mandatory Service Bulletin A310–53–2025 ..................................................................................... Service Bulletin A300–53–6006 ....................................................................................................... Date 04 05 06 3 July 18, 2007. October 13, 2006. August 3, 2006. March 24, 1989. Airbus Service Bulletin A300–53–6006, Revision 3, dated March 24, 1989, contains the following effective pages: Revision level shown on page Page Nos. 1, 29, 47, 48 ................................................................................................................................................ 2–28, 30–46, 49–52 ..................................................................................................................................... CPrice-Sewell on DSKGBLS3C1PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_ locations.html. Issued in Renton, Washington, on September 16, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–23094 Filed 9–28–09; 8:45 am] BILLING CODE 4910–13–P SUSQUEHANNA RIVER BASIN COMMISSION 18 CFR Parts 806 and 808 Review and Approval of Projects AGENCY: Susquehanna River Basin Commission. ACTION: Final rule. SUMMARY: This document contains amendments to the project review regulations of the Susquehanna River Basin Commission (Commission) including provisions restricting the use of docket reopening petitions to avoid abuses of process; amending the ‘‘Approval by Rule’’ (ABR) process to allow for project sponsors to utilize approved water sources at approved drilling pad sites without the need for modification of the ABR; clarifying that the public hearing requirement for rulemaking shall be applicable to the proposed rulemaking stage of that process; and further providing for the time period within which administrative appeals must be filed. These amendments were first proposed in a Notice of Proposed Rulemaking (NOPR) that appeared at 74 FR 31647 on July 2, 2009. DATES: These rules are effective on November 1, 2009. VerDate Nov<24>2008 15:02 Sep 28, 2009 Jkt 217001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 3 2 Date shown on page March 24, 1989. August 11, 1988. ADDRESSES: Susquehanna River Basin Commission, 1721 N. Front Street, Harrisburg, PA 17102–2391. FOR FURTHER INFORMATION CONTACT: Richard A. Cairo, General Counsel, telephone: 717–238–0423, ext. 306; fax: 717–238–2436; e-mail: rcairo@srbc.net. Also, for further information on the final rulemaking, visit the Commission’s Web site at http://www.srbc.net. SUPPLEMENTARY INFORMATION: Background and Purpose of Amendments The Commission convened public hearings on August 4, 2009, in Harrisburg, Pennsylvania and on August 5, 2009, in Elmira, New York. A written comment period was held open until August 15, 2009. Comments were received at both the hearings and during the comment period. A summary of the comments and the Commission’s responses thereto follows. Comments by Section, Part 806 Section 806.4 Projects Requiring Review and Approval Comment: The Commission’s proposal to require review and approval for any hydroelectric project regulated by the Federal Energy Regulatory Commission (FERC) and initiating a licensing or licensing amendment is defective and should not be adopted because: (1) As currently worded, the E:\FR\FM\29SER1.SGM 29SER1

Agencies

[Federal Register Volume 74, Number 187 (Tuesday, September 29, 2009)]
[Rules and Regulations]
[Pages 49805-49809]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-23094]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-174-AD; 
Amendment 39-16029; AD 2009-20-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-203 and -222 
Airplanes and Model A300 B4-620 Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. This 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:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03, 
amendment 39-5871] was issued to prevent development of damage, 
which was discovered during [a] fatigue test in the attachment 
angles of the rear pressure bulkhead (fuselage frame 80/82).

[[Page 49806]]

    Following the life extension activities linked to the A310 
program, the interval of inspection for A310-200 aircraft series was 
reduced from 12000 flight cycles (FC) to 9000 FC * * *.
    Some stress analysis conducted in the frame of the life 
extension activities of the A300-600 program leads the manufacturer 
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.
* * * * *

The unsafe condition is cracking in the attachment angles of the rear 
pressure bulkhead, which could result in failure of the rear pressure 
bulkhead. We are issuing this AD to require actions to correct the 
unsafe condition on these products.

DATES: This AD becomes effective November 3, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 3, 
2009.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on May 7, 2009 (74 FR 
21274), and proposed to supersede AD 88-06-03, Amendment 39-5871 (53 FR 
7730, March 10, 1988). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03] was 
issued to prevent development of damage, which was discovered during 
[a] fatigue test in the attachment angles of the rear pressure 
bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310 
program, the interval of inspection for A310-200 aircraft series was 
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the 
issuance of EASA AD 2007-0157, superseding DGAC France AD 86-102-
74(B).
    Some stress analysis conducted in the frame of the life 
extension activities of the A300-600 program leads the manufacturer 
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.
    EASA AD 2007-0297 superseded EASA AD 2007-0157, retaining for 
A310 aircraft the requirements of EASA AD 2007-0157 and requiring 
the application of Airbus Service Bulletin (SB) A300-53-6005 
Revision 4 on Airbus A300-600 aircraft, reducing the inspection 
interval from 12000 FC to 9000 FC.
    [EASA] AD [2007-0297] has been revised to remove an 
inappropriate reference regarding the normal inspection program from 
the Compliance section, Note 3.

The unsafe condition is cracking in the attachment angles of the rear 
pressure bulkhead, which could result in failure of the rear pressure 
bulkhead. The required actions include a modification of the rear 
pressure bulkhead to improve the fatigue life of the attachment angles 
at frame (FR) 80/82, and, for certain airplanes, repetitive inspections 
for cracks in the rear pressure bulkhead and repair if necessary.
    The modification includes installing additional attachment angles 
on the circumference of FR 80/82; installing a filler; installing 
additional supports between the aft pressure bulkhead and FR 80/82; 
installing an additional frame stiffener and support between the aft 
pressure bulkhead and FR 79 at stringer (STGR) 13; modifying the aft 
lavatories; applying surface protection to the modified area of the aft 
pressure bulkhead; modifying, reidentifying, and installing the heat 
and sound insulation in the area of STGR 9 and STGR 13 and between FR 
79 and FR 80/82, left and right; and for certain airplanes, doing 
related investigative and corrective actions if necessary.
    The related investigative action is doing a visual inspection 
around the entire circumference between FR 80/82 and the aft pressure 
bulkhead for damaged filler. The corrective action is removing any 
damaged filler and the adjacent area around the damage.
    You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Revise Paragraph (f)(4) of the NPRM

    Airbus requests that we revise paragraph (f)(4) of the NPRM. Airbus 
states that for the airplanes identified in paragraph (f)(4) of the 
NPRM, it is not necessary to do the actions in accordance with the 
service bulletins specified in paragraph (f)(4) of the NPRM. Airbus 
further states that those airplanes are affected by Airworthiness 
Limitation Item (ALI) Task 531919-01-1A, as specified in the service 
bulletins identified in paragraph (f)(4) of this AD and the MCAI.
    We agree with the commenter. The actions specified in paragraph 
(f)(4) of the NPRM are not required for the airplanes identified in 
that paragraph because those airplanes are already inspected in 
accordance with ALI Task 531919-01-1A, and no additional actions are 
necessary. We have confirmed with EASA that this is the intent of the 
MCAI. We have removed paragraph (f)(4) of the NPRM as it is 
unnecessary, and added a new Note 1 to this AD to clarify that no 
action is required by this AD for the airplanes discussed in this 
paragraph. We have re-identified the subsequent paragraphs accordingly.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect about 32 products of U.S. 
registry. We also estimate that it will take about 668 work-hours per 
product to comply with the basic requirements of this AD. The average 
labor rate is $80 per work-hour. Required parts will cost about $15,322 
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

[[Page 49807]]

higher than estimated here. Based on these figures, we estimate the 
cost of this AD to the U.S. operators to be $2,200,384, or $68,762 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-5871 (53 FR 
7730, March 10, 1988) and adding the following new AD:

2009-20-06 Airbus: Amendment 39-16029. Docket No. FAA-2009-0431; 
Directorate Identifier 2007-NM-174-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
3, 2009.

Affected ADs

    (b) This AD supersedes AD 88-06-03, Amendment 39-5871.

Applicability

    (c) This AD applies to Airbus Model A310-203 and -222 airplanes, 
and Model A300 B4-620 airplanes; certificated in any category; all 
serial numbers except airplanes on which Airbus Modification 05526 
has been incorporated in production.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    DGAC (Direction G[eacute]n[eacute]rale de l'Aviation Civile) 
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03, 
amendment 39-5871] was issued to prevent development of damage, 
which was discovered during [a] fatigue test in the attachment 
angles of the rear pressure bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310 
program, the interval of inspection for A310-200 aircraft series was 
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the 
issuance of EASA AD 2007-0157, superseding DGAC France AD 86-102-
74(B).
    Some stress analysis conducted in the frame of the life 
extension activities of the A300-600 program leads the manufacturer 
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.
    EASA AD 2007-0297 superseded EASA AD 2007-0157, retaining for 
A310 aircraft the requirements of EASA AD 2007-0157 and requiring 
the application of Airbus Service Bulletin (SB) A300-53-6005 
Revision 4 on Airbus A300-600 aircraft, reducing the inspection 
interval from 12000 FC to 9000 FC.
    [EASA] AD [2007-0297] has been revised to remove an 
inappropriate reference regarding the normal inspection program from 
the Compliance section, Note 3.

The unsafe condition is cracking in the attachment angles of the 
rear pressure bulkhead, which could result in failure of the rear 
pressure bulkhead. The required actions include a modification of 
the rear pressure bulkhead to improve the fatigue life of the 
attachment angles at frame (FR) 80/82; applicable related 
investigative and corrective actions; and, for certain airplanes, 
repetitive inspections for cracks in the rear pressure bulkhead and 
repair if necessary.

Requirements of This AD: Actions and Compliance

    (f) Unless already done, do the following actions.

Modification

    (1) Except as required by paragraph (f)(2) of this AD: Before 
the accumulation of 12,000 total flight cycles since first flight, 
or within 1,500 flight cycles after the effective date of this AD, 
whichever occurs later, modify the aft pressure bulkhead to improve 
the fatigue life of the attachment angles at frame 80/82 and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus 
Mandatory Service Bulletin A310-53-2025, Revision 06, dated August 
3, 2006; as applicable. Do all applicable related investigative and 
corrective actions before further flight.
    (2) For airplanes identified in paragraph (c) of AD 2006-22-03, 
amendment 39-14800: At the earlier of the compliance times specified 
in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions 
specified in paragraph (f)(1) of this AD.
    (i) Before the accumulation of 12,000 total flight cycles since 
first flight, or within 1,500 flight cycles after the effective date 
of this AD, whichever occurs later.
    (ii) At the compliance time specified in paragraph (h) of AD 
2006-22-03.

Inspections and Corrective Action

    (3) For airplanes on which the modification required by 
paragraph (f)(1) or (f)(2) of this AD is done after the accumulation 
of 6,000 total flight cycles since first flight: At the times 
specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an 
eddy current inspection for any cracking in the critical area of the 
rear pressure bulkhead between stringers 8 and 18, and repair all 
cracking before further flight, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-6005, Revision 04, dated July 18, 2007; or Airbus Mandatory 
Service Bulletin A310-53-2024, Revision 05, dated October 13, 2006; 
as applicable.

[[Page 49808]]

    (i) Before or concurrently with the modification required by 
paragraph (f)(1) or (f)(2) of this AD, as applicable; and
    (ii) Before the accumulation of 18,000 total flight cycles since 
first flight, or within 1,500 flight cycles after the effective date 
of this AD, whichever occurs later; and thereafter at intervals not 
to exceed 9,000 flight cycles.

    Note 1: For airplanes on which the modification required by 
paragraph (f)(1) or (f)(2) of this AD is done at or before the 
accumulation of 6,000 total flight cycles since first flight: No 
action is required by this AD. For these airplanes, refer to Airbus 
A300-600 ALI Task 531919-01-1A or Airbus A310 ALI Task 531919-01-1A, 
as applicable, for guidance on the normal inspection program.

    (4) Modifications done before the effective date of this AD in 
accordance with the service bulletins identified in Table 1 of this 
AD are acceptable for compliance with the requirements of paragraph 
(f)(1) and (f)(2) of this AD.

                          Table 1--Modifications Done Using Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                   Airbus Service
            Model--                  Bulletin--                Revision--                      Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes..........  A300-53-6006......  Original.....................  May 6, 1986.
                                 A300-53-6006......  1............................  September 19, 1986.
                                 A300-53-6006......  2............................  August 11, 1988.
A310-203 and -222 airplanes....  A310-53-2025......  Original.....................  April 21, 1986.
                                 A310-53-2025......  1............................  September 19, 1986.
                                 A310-53-2025......  2............................  February 16, 1987.
                                 A310-53-2025......  3............................  April 7, 1987.
                                 A310-53-2025......  4............................  October 20, 1987.
                                 A310-53-2025......  5............................  March 24, 1989.
----------------------------------------------------------------------------------------------------------------

    (5) Inspections done before the effective date of this AD in 
accordance with the service bulletins identified in Table 2 of this 
AD are acceptable for compliance with the requirements of paragraph 
(f)(3) of this AD.

                            Table 2--Inspections Done With Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                   Airbus Service
            Model--                  Bulletin--                Revision--                      Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes..........  A300-53-6005......  Original.....................  May 6, 1986.
                                 A300-53-6005......  1............................  June 20, 1986.
                                 A300-53-6005......  2............................  September 22, 1986.
                                 A300-53-6005......  3............................  April 22, 1987.
A310-203 and -222 airplanes....  A310-53-2024......  Original.....................  April 21, 1986.
                                 A310-53-2024......  1............................  June 20, 1986.
                                 A310-53-2024......  2............................  October 2, 1986.
                                 A310-53-2024......  3............................  February 17, 1987.
                                 A310-53-2024......  4............................  February 2, 1988.
----------------------------------------------------------------------------------------------------------------

    (6) Modification of the aft pressure bulkhead to improve the 
fatigue life of the attachment angles at frame (FR) 80/82 in 
accordance with paragraph (h) of AD 2006-22-03 is acceptable for 
compliance with the corresponding requirement of paragraphs (f)(1) 
and (f)(2) of this AD.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows. This AD includes a compliance time specified in 
paragraph (f)(2) of this AD for airplanes that are also affected by 
AD 2006-22-03. We realize that the requirements of this AD will 
necessitate that some operators do the modification required by 
paragraph (h) of AD 2006-22-03 early. However, accomplishing the 
modification within the compliance time specified in this AD is 
required to address cracking in the attachment angles of the rear 
pressure bulkhead, which could result in failure of the rear 
pressure bulkhead.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Tom 
Stafford, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office.
    (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 EASA Airworthiness Directive 2007-0297R1, 
dated September 17, 2008, and the service bulletins listed in Table 
3 of this AD, for related information.

                   Table 3--Related Service Bulletins
------------------------------------------------------------------------
   Airbus Service Bulletin       Revision                Date
------------------------------------------------------------------------
Airbus Mandatory Service                  04  July 18, 2007.
 Bulletin A300-53-6005.
Airbus Mandatory Service                  05  October 13, 2006.
 Bulletin A310-53-2024.
Airbus Mandatory Service                  06  August 3, 2006.
 Bulletin A310-53-2025.

[[Page 49809]]

 
Airbus Service Bulletin A300-              3  March 24, 1989.
 53-6006.
------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the service information contained in Table 4 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.

               Table 4--Material Incorporated by Reference
------------------------------------------------------------------------
   Airbus Service Bulletin       Revision                Date
------------------------------------------------------------------------
Airbus Mandatory Service                  04  July 18, 2007.
 Bulletin A300-53-6005.
Airbus Mandatory Service                  05  October 13, 2006.
 Bulletin A310-53-2024.
Airbus Mandatory Service                  06  August 3, 2006.
 Bulletin A310-53-2025.
Airbus Service Bulletin A300-              3  March 24, 1989.
 53-6006.
------------------------------------------------------------------------

    Airbus Service Bulletin A300-53-6006, Revision 3, dated March 
24, 1989, contains the following effective pages:

------------------------------------------------------------------------
                              Revision level
          Page Nos.            shown on page      Date shown on page
------------------------------------------------------------------------
1, 29, 47, 48...............               3   March 24, 1989.
2-28, 30-46, 49-52..........               2   August 11, 1988.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on September 16, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-23094 Filed 9-28-09; 8:45 am]
BILLING CODE 4910-13-P