Airworthiness Directives; Airbus Model A300-600 and A310 Airplanes, 16685-16689 [2010-7459]

Download as PDF Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. (1) For Group 1, Configuration 1 airplanes, as identified in Boeing Alert Service Bulletin 777–57A0069, dated November 5, 2009: Before the accumulation of 3,500 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. (2) For Group 1, Configuration 2 airplanes and Group 2 airplanes, as identified in Boeing Alert Service Bulletin 777–57A0069, dated November 5, 2009, on which a crack was found in the cutout keyway when the cutout keyway was changed: Within 1,125 days after the effective date of this AD. Note 1: For Group 1, Configuration 2 airplanes and Group 2 airplanes, as identified in Boeing Alert Service Bulletin 777– 57A0069, dated November 5, 2009, on which no crack was found in the cutout keyway when the cutout keyway was changed: No further action is required by this AD. Exceptions to Service Bulletin (h) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 777–57A0069, dated November 5, 2009, specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (i) of this AD. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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: Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6452; fax (425) 917–6590. Or, e-mail information to 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. (2) 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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. VerDate Nov<24>2008 14:33 Apr 01, 2010 Jkt 220001 Issued in Renton, Washington, on March 25, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–7458 Filed 4–1–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0281; Directorate Identifier 2009–NM–184–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300–600 and A310 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: Surface defects were visually detected on the rudder of one Airbus A319 and one A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were the result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A310 and A300–600 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. 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 May 17, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 16685 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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 https://www.airbus.com. You may review copies of the referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 this proposed AD, 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. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 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–2010–0281; Directorate Identifier 2009–NM–184–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 have lengthened the 30-day comment period for proposed ADs that address MCAI originated by aviation authorities of other countries to provide E:\FR\FM\02APP1.SGM 02APP1 16686 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs. We will post all comments we receive, without change, to https:// www.regulations.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 EASA Airworthiness Directive 2010–0002, dated January 5, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 Surface defects were visually detected on the rudder of one Airbus A319 and one A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were the result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A310 and A300–600 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. To address this unsafe condition [this EASA AD] requires inspections of specific areas and, depending on findings, the application of corrective actions for those rudders where production reworks have been identified. This * * * [EASA] AD * * * also requires for the vacuum loss hole restoration: —A local ultrasonic inspection for reinforced area instead of the local thermographic inspection, which is maintained for nonreinforced areas, and —Additional work performance for rudders on which this thermographic inspection has been performed in the reinforced area. The inspections include vacuum loss inspections and elasticity laminate checker inspections for defects including de-bonding between the skin and honeycomb core of the rudder, and ultrasonic inspections for rudders on which temporary restoration with resin or permanent vacuum loss hole restoration has been performed. The corrective action is contacting the manufacturer for repair instructions and doing the repair. We are considering similar rulemaking action on Models A319 and A321 airplanes. You may VerDate Nov<24>2008 14:33 Apr 01, 2010 Jkt 220001 obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued All Operators Telex (AOT) A300–55A6047, Revision 02, dated October 12, 2009; and AOT A310– 55A2048, Revision 02, dated October 12, 2009. 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 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 194 products of U.S. registry. We also estimate that it would take about 4 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $65,960, or $340 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: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 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, Incorporation by reference, 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 No. FAA–2010–0281; Directorate Identifier 2009–NM–184–AD. E:\FR\FM\02APP1.SGM 02APP1 16687 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules Comments Due Date (a) We must receive comments by May 17, 2010. Applicability (c) This AD applies to Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes; and Model A310–203, –204, –221, –222, –304, –322, –324, and –325 Affected ADs (b) None. airplanes; certificated in any category; equipped with carbon fiber reinforced plastic rudders having part numbers and serial numbers listed in Table 1 of this AD. TABLE 1—RUDDER INFORMATION Affected rudder serial No. Rudder part No. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 A554–71500–016–91 A554–71500–016–91 A554–71500–016–91 A554–71500–016–91 A554–71500–016–91 A554–71500–014–00 A554–71500–014–00 A554–71500–016–00 A554–71500–016–00 A554–71500–016–00 A554–71500–026–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–000–00 A554–71710–002–00 A554–71710–002–00 A554–71710–002–00 A554–71710–002–00 A554–71710–002–00 A554–71710–002–00 A554–71710–002–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 A554–71710–004–00 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Subject (d) Air Transport Association (ATA) of America Code 55: Stabilizers. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Surface defects were visually detected on the rudder of one Airbus A319 and one A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation VerDate Nov<24>2008 14:33 Apr 01, 2010 Jkt 220001 confirmed that the defects were the result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A310 and A300–600 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. To address this unsafe condition [this EASA AD] requires inspections of specific PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 HF–1017 HF–1020 HF–1059 HF–1061 HF–1064 HF–1087 HF–1119 HF–1189 HF–1203 HF–1266 TS–1405 TS–2001 TS–2004 TS–2007 TS–2009 TS–2011 TS–2012 TS–2013 TS–2014 TS–2016 TS–2017 TS–2018 TS–2020 TS–2021 TS–2022 TS–2024 TS–2025 TS–2026 TS–2028 TS–2029 TS–2031 TS–2032 TS–2035 TS–2040 TS–2041 TS–2044 TS–2046 TS–2050 TS–2056 TS–2058 TS–2060 TS–2062 TS–2065 TS–2066 TS–2074 TS–2075 TS–2076 TS–2079 ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... Core density 24 kg/m3 Yes. No. No. No. No. Yes. Yes. Yes. Yes. Yes. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. No. areas and, depending on findings, the application of corrective actions for those rudders where production reworks have been identified. This * * * [EASA] AD * * * also requires for the vacuum loss hole restoration: —A local ultrasonic inspection for reinforced area instead of the local thermographic inspection, which is maintained for nonreinforced areas, and —Additional work performance for rudders on which this thermographic inspection has been performed in the reinforced area. E:\FR\FM\02APP1.SGM 02APP1 16688 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules The inspections include vacuum loss inspections and elasticity laminate checker inspections for defects including de-bonding between the skin and honeycomb core of the rudder, and ultrasonic inspections for rudders on which temporary restoration with resin or permanent vacuum loss hole restoration has been performed. The corrective action is contacting the manufacturer for repair instructions and doing the repair. We are considering similar rulemaking action on Models A319 and A321 airplanes. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions and Compliance (g) For rudders with a honeycomb core density of 24 kg/m3, as identified in Table 1 of this AD, do the actions required in paragraphs (g)(1) through (g)(10) of this AD, in accordance with Airbus All Operators Telex (AOT) A310–55A2048 or A300– 55A6047, both Revision 02, both dated October 12, 2009, as applicable. (1) In the reinforced location: Within 8 months after the effective date of this AD, do a vacuum loss inspection to detect defects including de-bonding. (2) In the trailing edge location: Within 24 months after the effective date of this AD, do an elasticity laminate checker inspection to detect defects including de-bonding. (3) Repeat the inspection required by paragraph (g)(2) of this AD two times at intervals not to exceed 4,500 flight cycles, but not fewer than 4,000 flight cycles from the last inspection. (4) In other locations (lower rib/upper edge/leading edge/other locations): Within 8 months after the effective date of this AD, do an elasticity laminate checker inspection to detect defects including de-bonding. (5) Repeat the inspection required by paragraph (g)(4) of this AD at intervals not to exceed 8 months from the last inspection. (6) Within 24 months after the effective date of this AD, do a vacuum loss inspection on the other locations (lower rib/upper edge/ leading edge/other locations) to detect defects including de-bonding. (7) Accomplishment of the inspection required by paragraph (g)(6) of this AD terminates the initial and repetitive inspections required by paragraphs (g)(4) and (g)(5) of this AD. (8) If any defect is found during any inspection required by paragraph (g)(1), (g)(2), (g)(4), or (g)(6) of this AD, before further flight, contact Airbus for repair instructions and do the repair. (9) If no defects are found during any inspection required by paragraphs (g)(1) and (g)(6) of this AD, before further flight, restore the vacuum loss holes with temporary restoration with self-adhesive patches, temporary restoration with resin, or permanent restoration with resin and surface VerDate Nov<24>2008 14:33 Apr 01, 2010 Jkt 220001 protection, and repeat the inspection required by paragraph (g)(3) of this AD at intervals not to exceed 4,500 flight cycles until permanent restoration is completed. (10) If any defect is found during any inspection required by paragraphs (g)(1), (g)(2), (g)(4), and (g)(6) of this AD, at the applicable time in paragraph (g)(10)(i) or (g)(10)(ii) of this AD: Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3, Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to region1.StructureRepairSupport@airbus.com, region2.StructureRepairSupport@airbus.com, or region3.StructureRepairSupport@airbus.com. (i) Inspections done before the effective date of this AD: Within 30 days after the effective date of this AD. (ii) Inspections done on or after the effective date of this AD: Within 30 days after accomplishment of the inspection. (11) If no defect is found during any inspection required by paragraphs (g)(1), (g)(2), (g)(4), and (g)(6) of this AD, at the applicable time in (g)(10)(i) or (g)(10)(ii): Report the inspection results to Airbus SAS, Jean-Luc BOITEUX, SEES1, Customer Services, fax (0) 5 61 93 36 14; or e-mail to jean-luc.j.boiteux@airbus.com. (h) For rudders not having a honeycomb core density of 24 kg/m3, as identified in Table 1 of this AD, do the actions required in paragraph (h)(1) through (h)(10) of this AD in accordance with Airbus AOT A310– 55A2048 or AOT A300–55A6047, both Revision 02, both dated October 12, 2009, as applicable. (1) In the reinforced location: Within 8 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 8 months after the effective date of this AD, whichever occurs later, do a vacuum loss inspection to detect defects including de-bonding. (2) In the trailing edge location: Within 24 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 24 months after the effective date of this AD, whichever occurs later, do an elasticity laminate checker inspection to detect defects including de-bonding. (3) Repeat the inspection required by paragraph (h)(2) of this AD two times at intervals not to exceed 4,500 flight cycles, but not fewer than 4,000 flight cycles from the last inspection. (4) In other locations (lower rib/upper edge/leading edge/other locations): Within 8 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 8 months after the effective date of this AD, whichever occurs later, do an elasticity laminate checker inspection to detect defects including de-bonding. (5) Repeat the inspection required by paragraph (h)(4) of this AD at intervals not to exceed 8 months from the last inspection. (6) Within 24 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 24 months after the PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 effective date of this AD, whichever occurs later, do a vacuum loss inspection on the other locations (lower rib/upper edge/leading edge/other location) to detect defects including de-bonding. (7) Accomplishment of the inspection required by paragraph (h)(6) of this AD terminates the initial and repetitive inspections required by paragraphs (h)(4) and (h)(5) of this AD. (8) If any defect is found during any inspection required by paragraph (h)(1), (h)(2), (h)(4), or (h)(6) of this AD, before further flight, contact Airbus for repair instructions and do the repair. (9) If no defects are found during the inspections required by paragraphs (h)(1) and (h)(6) of this AD, before further flight, restore the vacuum loss holes with the temporary restoration with self adhesive patches, temporary restoration with resin, or permanent restoration with resin and surface protection, and repeat the inspection required by paragraph (h)(3) of this AD at intervals not to exceed 4,500 flight cycles until permanent restoration is completed. (10) If any defect is found during any inspection required by paragraphs (h)(1), (h)(2), (h)(4), and (h)(6) of this AD, at the applicable time in paragraph (h)(10)(i) or (h)(10)(ii) of this AD: Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3, Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to region1.StructureRepairSupport@airbus.com, region2.StructureRepairSupport@airbus.com, or region3.StructureRepairSupport@airbus.com. (i) Inspections done before the effective date of this AD: Within 30 days after the effective date of this AD. (ii) Inspections done on or after the effective date of this AD: Within 30 days after accomplishment of the inspection. (11) If no defect is found during any inspection required by paragraphs (h)(1), (h)(2), (h)(4), and (h)(6) of this AD, at the applicable time in (h)(10)(i) or (h)(10)(ii): Report the inspection results to Airbus SAS, Jean-Luc BOITEUX, SEES1, Customer Services, fax (0) 5 61 93 36 14; or e-mail to jean-luc.j.boiteux@airbus.com. (i) Actions done before the effective date of this AD, in accordance with the service information listed in Table 2 of this AD, are acceptable for compliance with the requirements of paragraphs (g) and (h) of this AD for the areas inspected, for any rudder listed in Table 1 of this AD. (j) Additional areas requiring inspection for all airplanes are defined in Airbus AOT A310–55A2048 or AOT A300–55A6047, both Revision 02, both dated October 12, 2009, as applicable. For these additional areas, do the actions required in paragraphs (g) and (h) of this AD, as applicable, at the times specified in those paragraphs. For all areas, do the repetitive inspections required by paragraphs (g) and (h) of this AD as applicable at the times specified in those paragraphs. E:\FR\FM\02APP1.SGM 02APP1 16689 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules TABLE 2—CREDIT SERVICE INFORMATION Airbus AOT— A300–55A6047 A300–55A6047 A310–55A2048 A310–55A2048 Revision— ............................................................ ............................................................ ............................................................ ............................................................ (k) For rudders on which temporary restoration with resin or permanent vacuum loss hole restoration has been done in accordance with the applicable service bulletin in Table 2 of this AD, as required in paragraph (g)(9) or (h)(9) of this AD, before the effective date of this AD: Within 4,500 flight cycles from the restoration date, do an ultrasonic inspection for defects, including debonding of the reinforced area, in accordance with Airbus AOT A310–55A2048 or AOT A300–55A6047, both Revision 02, both dated October 12, 2009, as applicable. If any defect is found, before further flight, contact Airbus for repair instructions and do the repair. (l) After the effective date of this AD, no person may install any rudder listed in Table 1 of this AD on any airplane, unless the rudder has been inspected and all applicable corrective actions have been done in accordance with paragraph (g) or (h) of this AD. FAA AD Differences wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 14:33 Apr 01, 2010 Jkt 220001 approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (n) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0002, dated January 5, 2010; and Airbus AOT A310–55A2048, Revision 02, dated October 12, 2009, or Airbus AOT A300–55A6047, Revision 02, dated October 12, 2009; for related information. Issued in Renton, Washington, on March 25, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–7459 Filed 4–1–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 Other FAA AD Provisions (m) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; 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. The AMOC approval letter must specifically reference this AD. (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 VerDate Nov<24>2008 Original ........................................................................ 01 ................................................................................ Original ........................................................................ 01 ................................................................................ Federal Aviation Administration Note 1: This AD differs from the MCAI and/or service information as follows: No differences. [Docket No. FAA–2010–0279; Directorate Identifier 2009–NM–148–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series 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: Surface defects were visually detected on the rudder of one A319 and one A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were a result of de-bonding between the skin and honeycomb core. An extended de-bonding, if not detected and corrected, may degrade the structural PO 00000 Dated— Frm 00014 Fmt 4702 Sfmt 4702 May 11, 2009. July 8, 2009. May 11, 2009. July 8, 2009. integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. 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 May 17, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https:// www.airbus.com. You may review copies of the referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 this proposed AD, 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. E:\FR\FM\02APP1.SGM 02APP1

Agencies

[Federal Register Volume 75, Number 63 (Friday, April 2, 2010)]
[Proposed Rules]
[Pages 16685-16689]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-7459]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0281; Directorate Identifier 2009-NM-184-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 and A310 
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: Surface defects were visually detected on the rudder of 
one Airbus A319 and one A321 in-service aeroplane. Investigation has 
determined that the defects reported on both rudders corresponded to 
areas that had been reworked in production. The investigation confirmed 
that the defects were the result of de-bonding between the skin and 
honeycomb core. Such reworks were also performed on some rudders fitted 
on A310 and A300-600 aeroplanes. An extended de-bonding, if not 
detected and corrected, may degrade the structural integrity of the 
rudder. The loss of the rudder leads to degradation of the handling 
qualities and reduces the controllability of the aeroplane.
    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 May 17, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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 https://www.airbus.com. You may review copies of the referenced 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 this proposed AD, 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.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

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-2010-0281; 
Directorate Identifier 2009-NM-184-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 have lengthened the 30-day comment period for proposed ADs that 
address MCAI originated by aviation authorities of other countries to 
provide

[[Page 16686]]

adequate time for interested parties to submit comments. The comment 
period for these proposed ADs is now typically 45 days, which is 
consistent with the comment period for domestic transport ADs.
    We will post all comments we receive, without change, to https://www.regulations.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 EASA 
Airworthiness Directive 2010-0002, dated January 5, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Surface defects were visually detected on the rudder of one 
Airbus A319 and one A321 in-service aeroplane. Investigation has 
determined that the defects reported on both rudders corresponded to 
areas that had been reworked in production. The investigation 
confirmed that the defects were the result of de-bonding between the 
skin and honeycomb core. Such reworks were also performed on some 
rudders fitted on A310 and A300-600 aeroplanes.
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
    To address this unsafe condition [this EASA AD] requires 
inspections of specific areas and, depending on findings, the 
application of corrective actions for those rudders where production 
reworks have been identified.
    This * * * [EASA] AD * * * also requires for the vacuum loss 
hole restoration:

--A local ultrasonic inspection for reinforced area instead of the 
local thermographic inspection, which is maintained for non-
reinforced areas, and
--Additional work performance for rudders on which this 
thermographic inspection has been performed in the reinforced area.

The inspections include vacuum loss inspections and elasticity laminate 
checker inspections for defects including de-bonding between the skin 
and honeycomb core of the rudder, and ultrasonic inspections for 
rudders on which temporary restoration with resin or permanent vacuum 
loss hole restoration has been performed. The corrective action is 
contacting the manufacturer for repair instructions and doing the 
repair. We are considering similar rulemaking action on Models A319 and 
A321 airplanes. You may obtain further information by examining the 
MCAI in the AD docket.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-55A6047, Revision 
02, dated October 12, 2009; and AOT A310-55A2048, Revision 02, dated 
October 12, 2009. 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 
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 194 products of U.S. registry. We also estimate that 
it would take about 4 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $65,960, or $340 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, Incorporation by 
reference, 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 No. FAA-2010-0281; Directorate Identifier 2009-NM-
184-AD.

[[Page 16687]]

Comments Due Date

    (a) We must receive comments by May 17, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F 
airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; certificated in any category; equipped with 
carbon fiber reinforced plastic rudders having part numbers and 
serial numbers listed in Table 1 of this AD.

                                           Table 1--Rudder Information
----------------------------------------------------------------------------------------------------------------
              Rudder part No.                   Affected rudder  serial No.          Core density 24 kg/m\3\
----------------------------------------------------------------------------------------------------------------
A554-71500-016-91..........................  HF-1017..........................  Yes.
A554-71500-016-91..........................  HF-1020..........................  No.
A554-71500-016-91..........................  HF-1059..........................  No.
A554-71500-016-91..........................  HF-1061..........................  No.
A554-71500-016-91..........................  HF-1064..........................  No.
A554-71500-014-00..........................  HF-1087..........................  Yes.
A554-71500-014-00..........................  HF-1119..........................  Yes.
A554-71500-016-00..........................  HF-1189..........................  Yes.
A554-71500-016-00..........................  HF-1203..........................  Yes.
A554-71500-016-00..........................  HF-1266..........................  Yes.
A554-71500-026-00..........................  TS-1405..........................  No.
A554-71710-000-00..........................  TS-2001..........................  No.
A554-71710-000-00..........................  TS-2004..........................  No.
A554-71710-000-00..........................  TS-2007..........................  No.
A554-71710-000-00..........................  TS-2009..........................  No.
A554-71710-000-00..........................  TS-2011..........................  No.
A554-71710-000-00..........................  TS-2012..........................  No.
A554-71710-000-00..........................  TS-2013..........................  No.
A554-71710-000-00..........................  TS-2014..........................  No.
A554-71710-000-00..........................  TS-2016..........................  No.
A554-71710-000-00..........................  TS-2017..........................  No.
A554-71710-000-00..........................  TS-2018..........................  No.
A554-71710-000-00..........................  TS-2020..........................  No.
A554-71710-000-00..........................  TS-2021..........................  No.
A554-71710-000-00..........................  TS-2022..........................  No.
A554-71710-000-00..........................  TS-2024..........................  No.
A554-71710-000-00..........................  TS-2025..........................  No.
A554-71710-000-00..........................  TS-2026..........................  No.
A554-71710-000-00..........................  TS-2028..........................  No.
A554-71710-000-00..........................  TS-2029..........................  No.
A554-71710-002-00..........................  TS-2031..........................  No.
A554-71710-002-00..........................  TS-2032..........................  No.
A554-71710-002-00..........................  TS-2035..........................  No.
A554-71710-002-00..........................  TS-2040..........................  No.
A554-71710-002-00..........................  TS-2041..........................  No.
A554-71710-002-00..........................  TS-2044..........................  No.
A554-71710-002-00..........................  TS-2046..........................  No.
A554-71710-004-00..........................  TS-2050..........................  No.
A554-71710-004-00..........................  TS-2056..........................  No.
A554-71710-004-00..........................  TS-2058..........................  No.
A554-71710-004-00..........................  TS-2060..........................  No.
A554-71710-004-00..........................  TS-2062..........................  No.
A554-71710-004-00..........................  TS-2065..........................  No.
A554-71710-004-00..........................  TS-2066..........................  No.
A554-71710-004-00..........................  TS-2074..........................  No.
A554-71710-004-00..........................  TS-2075..........................  No.
A554-71710-004-00..........................  TS-2076..........................  No.
A554-71710-004-00..........................  TS-2079..........................  No.
----------------------------------------------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 55: 
Stabilizers.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Surface defects were visually detected on the rudder of one 
Airbus A319 and one A321 in-service aeroplane. Investigation has 
determined that the defects reported on both rudders corresponded to 
areas that had been reworked in production. The investigation 
confirmed that the defects were the result of de-bonding between the 
skin and honeycomb core. Such reworks were also performed on some 
rudders fitted on A310 and A300-600 aeroplanes.
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
    To address this unsafe condition [this EASA AD] requires 
inspections of specific areas and, depending on findings, the 
application of corrective actions for those rudders where production 
reworks have been identified.
    This * * * [EASA] AD * * * also requires for the vacuum loss 
hole restoration:

--A local ultrasonic inspection for reinforced area instead of the 
local thermographic inspection, which is maintained for non-
reinforced areas, and
--Additional work performance for rudders on which this 
thermographic inspection has been performed in the reinforced area.


[[Page 16688]]


The inspections include vacuum loss inspections and elasticity 
laminate checker inspections for defects including de-bonding 
between the skin and honeycomb core of the rudder, and ultrasonic 
inspections for rudders on which temporary restoration with resin or 
permanent vacuum loss hole restoration has been performed. The 
corrective action is contacting the manufacturer for repair 
instructions and doing the repair. We are considering similar 
rulemaking action on Models A319 and A321 airplanes.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Actions and Compliance

    (g) For rudders with a honeycomb core density of 24 kg/m\3\, as 
identified in Table 1 of this AD, do the actions required in 
paragraphs (g)(1) through (g)(10) of this AD, in accordance with 
Airbus All Operators Telex (AOT) A310-55A2048 or A300-55A6047, both 
Revision 02, both dated October 12, 2009, as applicable.
    (1) In the reinforced location: Within 8 months after the 
effective date of this AD, do a vacuum loss inspection to detect 
defects including de-bonding.
    (2) In the trailing edge location: Within 24 months after the 
effective date of this AD, do an elasticity laminate checker 
inspection to detect defects including de-bonding.
    (3) Repeat the inspection required by paragraph (g)(2) of this 
AD two times at intervals not to exceed 4,500 flight cycles, but not 
fewer than 4,000 flight cycles from the last inspection.
    (4) In other locations (lower rib/upper edge/leading edge/other 
locations): Within 8 months after the effective date of this AD, do 
an elasticity laminate checker inspection to detect defects 
including de-bonding.
    (5) Repeat the inspection required by paragraph (g)(4) of this 
AD at intervals not to exceed 8 months from the last inspection.
    (6) Within 24 months after the effective date of this AD, do a 
vacuum loss inspection on the other locations (lower rib/upper edge/
leading edge/other locations) to detect defects including de-
bonding.
    (7) Accomplishment of the inspection required by paragraph 
(g)(6) of this AD terminates the initial and repetitive inspections 
required by paragraphs (g)(4) and (g)(5) of this AD.
    (8) If any defect is found during any inspection required by 
paragraph (g)(1), (g)(2), (g)(4), or (g)(6) of this AD, before 
further flight, contact Airbus for repair instructions and do the 
repair.
    (9) If no defects are found during any inspection required by 
paragraphs (g)(1) and (g)(6) of this AD, before further flight, 
restore the vacuum loss holes with temporary restoration with self-
adhesive patches, temporary restoration with resin, or permanent 
restoration with resin and surface protection, and repeat the 
inspection required by paragraph (g)(3) of this AD at intervals not 
to exceed 4,500 flight cycles until permanent restoration is 
completed.
    (10) If any defect is found during any inspection required by 
paragraphs (g)(1), (g)(2), (g)(4), and (g)(6) of this AD, at the 
applicable time in paragraph (g)(10)(i) or (g)(10)(ii) of this AD: 
Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3, 
Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to 
region1.StructureRepairSupport@airbus.com, 
region2.StructureRepairSupport@airbus.com, or 
region3.StructureRepairSupport@airbus.com.
    (i) Inspections done before the effective date of this AD: 
Within 30 days after the effective date of this AD.
    (ii) Inspections done on or after the effective date of this AD: 
Within 30 days after accomplishment of the inspection.
    (11) If no defect is found during any inspection required by 
paragraphs (g)(1), (g)(2), (g)(4), and (g)(6) of this AD, at the 
applicable time in (g)(10)(i) or (g)(10)(ii): Report the inspection 
results to Airbus SAS, Jean-Luc BOITEUX, SEES1, Customer Services, 
fax (0) 5 61 93 36 14; or e-mail to jean-luc.j.boiteux@airbus.com.
    (h) For rudders not having a honeycomb core density of 24 kg/
m\3\, as identified in Table 1 of this AD, do the actions required 
in paragraph (h)(1) through (h)(10) of this AD in accordance with 
Airbus AOT A310-55A2048 or AOT A300-55A6047, both Revision 02, both 
dated October 12, 2009, as applicable.
    (1) In the reinforced location: Within 8 months after the rudder 
has accumulated 13,000 flight cycles since first installation, or 
within 8 months after the effective date of this AD, whichever 
occurs later, do a vacuum loss inspection to detect defects 
including de-bonding.
    (2) In the trailing edge location: Within 24 months after the 
rudder has accumulated 13,000 flight cycles since first 
installation, or within 24 months after the effective date of this 
AD, whichever occurs later, do an elasticity laminate checker 
inspection to detect defects including de-bonding.
    (3) Repeat the inspection required by paragraph (h)(2) of this 
AD two times at intervals not to exceed 4,500 flight cycles, but not 
fewer than 4,000 flight cycles from the last inspection.
    (4) In other locations (lower rib/upper edge/leading edge/other 
locations): Within 8 months after the rudder has accumulated 13,000 
flight cycles since first installation, or within 8 months after the 
effective date of this AD, whichever occurs later, do an elasticity 
laminate checker inspection to detect defects including de-bonding.
    (5) Repeat the inspection required by paragraph (h)(4) of this 
AD at intervals not to exceed 8 months from the last inspection.
    (6) Within 24 months after the rudder has accumulated 13,000 
flight cycles since first installation, or within 24 months after 
the effective date of this AD, whichever occurs later, do a vacuum 
loss inspection on the other locations (lower rib/upper edge/leading 
edge/other location) to detect defects including de-bonding.
    (7) Accomplishment of the inspection required by paragraph 
(h)(6) of this AD terminates the initial and repetitive inspections 
required by paragraphs (h)(4) and (h)(5) of this AD.
    (8) If any defect is found during any inspection required by 
paragraph (h)(1), (h)(2), (h)(4), or (h)(6) of this AD, before 
further flight, contact Airbus for repair instructions and do the 
repair.
    (9) If no defects are found during the inspections required by 
paragraphs (h)(1) and (h)(6) of this AD, before further flight, 
restore the vacuum loss holes with the temporary restoration with 
self adhesive patches, temporary restoration with resin, or 
permanent restoration with resin and surface protection, and repeat 
the inspection required by paragraph (h)(3) of this AD at intervals 
not to exceed 4,500 flight cycles until permanent restoration is 
completed.
    (10) If any defect is found during any inspection required by 
paragraphs (h)(1), (h)(2), (h)(4), and (h)(6) of this AD, at the 
applicable time in paragraph (h)(10)(i) or (h)(10)(ii) of this AD: 
Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3, 
Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to 
region1.StructureRepairSupport@airbus.com, 
region2.StructureRepairSupport@airbus.com, or 
region3.StructureRepairSupport@airbus.com.
    (i) Inspections done before the effective date of this AD: 
Within 30 days after the effective date of this AD.
    (ii) Inspections done on or after the effective date of this AD: 
Within 30 days after accomplishment of the inspection.
    (11) If no defect is found during any inspection required by 
paragraphs (h)(1), (h)(2), (h)(4), and (h)(6) of this AD, at the 
applicable time in (h)(10)(i) or (h)(10)(ii): Report the inspection 
results to Airbus SAS, Jean-Luc BOITEUX, SEES1, Customer Services, 
fax (0) 5 61 93 36 14; or e-mail to jean-luc.j.boiteux@airbus.com.
    (i) Actions done before the effective date of this AD, in 
accordance with the service information listed in Table 2 of this 
AD, are acceptable for compliance with the requirements of 
paragraphs (g) and (h) of this AD for the areas inspected, for any 
rudder listed in Table 1 of this AD.
    (j) Additional areas requiring inspection for all airplanes are 
defined in Airbus AOT A310-55A2048 or AOT A300-55A6047, both 
Revision 02, both dated October 12, 2009, as applicable. For these 
additional areas, do the actions required in paragraphs (g) and (h) 
of this AD, as applicable, at the times specified in those 
paragraphs. For all areas, do the repetitive inspections required by 
paragraphs (g) and (h) of this AD as applicable at the times 
specified in those paragraphs.

[[Page 16689]]



                                       Table 2--Credit Service Information
----------------------------------------------------------------------------------------------------------------
             Airbus AOT--                     Revision--                             Dated--
----------------------------------------------------------------------------------------------------------------
A300-55A6047.........................  Original...............  May 11, 2009.
A300-55A6047.........................  01.....................  July 8, 2009.
A310-55A2048.........................  Original...............  May 11, 2009.
A310-55A2048.........................  01.....................  July 8, 2009.
----------------------------------------------------------------------------------------------------------------

     (k) For rudders on which temporary restoration with resin or 
permanent vacuum loss hole restoration has been done in accordance 
with the applicable service bulletin in Table 2 of this AD, as 
required in paragraph (g)(9) or (h)(9) of this AD, before the 
effective date of this AD: Within 4,500 flight cycles from the 
restoration date, do an ultrasonic inspection for defects, including 
debonding of the reinforced area, in accordance with Airbus AOT 
A310-55A2048 or AOT A300-55A6047, both Revision 02, both dated 
October 12, 2009, as applicable. If any defect is found, before 
further flight, contact Airbus for repair instructions and do the 
repair.
    (l) After the effective date of this AD, no person may install 
any rudder listed in Table 1 of this AD on any airplane, unless the 
rudder has been inspected and all applicable corrective actions have 
been done in accordance with paragraph (g) or (h) of this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (m) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2125; 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. The AMOC approval letter must 
specifically reference this AD.
    (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.

Related Information

    (n) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2010-0002, dated January 5, 2010; and Airbus 
AOT A310-55A2048, Revision 02, dated October 12, 2009, or Airbus AOT 
A300-55A6047, Revision 02, dated October 12, 2009; for related 
information.

    Issued in Renton, Washington, on March 25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-7459 Filed 4-1-10; 8:45 am]
BILLING CODE 4910-13-P

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