Airworthiness Directives; Airbus Model A380-841, -842, and -861 Airplanes, 7931-7934 [2010-3121]

Download as PDF Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2848; 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 (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 (h) Refer to MCAI Brazilian Airworthiness Directive 2008–10–03, effective October 21, 2008; and Embraer Service Bulletin 190–57– 0023, dated June 9, 2008; for related information. mstockstill on DSKH9S0YB1PROD with RULES Material Incorporated by Reference (i) You must use Embraer Service Bulletin 190–57–0023, dated June 9, 2008, as applicable, 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 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro ˜ Faria Lima, 2170—Putim—12227–901 Sao Jose dos Campos—SP—BRASIL; telephone: +55 12 3927–5852 or +55 12 3309–0732; fax: +55 12 3927–7546; e-mail: distrib@embraer.com.br; Internet: https:// www.flyembraer.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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on February 5, 2010. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–3116 Filed 2–22–10; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 16:17 Feb 22, 2010 Jkt 220001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0038; Directorate Identifier 2009–NM–110–AD; Amendment 39–16203; AD 2010–04–10] RIN 2120–AA64 Airworthiness Directives; Airbus Model A380–841, –842, and –861 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is 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: During the flight test campaign of the A380–861 model (Engine Alliance powered), some cracks were found on the Movable Flap Track Fairing number 6 (MFTF#6). These cracks were located at the pivot attachment support-ring and at the U-frame in the attachment area to aft-kinematic. In addition, delamination has been observed within the monolithic Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot support-ring. This condition, if not corrected, could lead to in-flight loss of the MFTF#6, potentially resulting in injuries to persons on the ground. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective March 10, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 10, 2010. On May 28, 2009 (74 FR 22422, May 13, 2009), the Director of the Federal Register approved the incorporation by reference of a certain other publication listed in the AD. We must receive comments on this AD by April 9, 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– PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 7931 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. 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 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion On May 1, 2009, the FAA issued AD 2009–10–07, Amendment 39–15902 (74 FR 22422, May 13, 2009). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued that AD, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0152, dated July 14, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During the flight test campaign of the A380–861 model (Engine Alliance powered), some cracks were found on the Movable Flap Track Fairing number 6 (MFTF#6). These cracks were located at the pivot attachment support-ring and at the U-frame in the attachment area to aft-kinematic. In addition, delamination has been observed within the monolithic Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot support-ring. This condition, if not corrected, could lead to in-flight loss of the MFTF#6, potentially resulting in injuries to persons on the ground. To prevent the risk of a MFTF#6 detachment, EASA AD 2008–0216 (which corresponds to FAA AD 2009–10–07) required an inspection programme in order to E:\FR\FM\23FER1.SGM 23FER1 7932 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations detect cracks before they become critical and in case of findings to replace the MFTF#6. This AD, which supersedes EASA AD 2008–0216: • Cancels the MFTF#6 General Visual Inspection requirement, • Refers to Airbus Service Bulletin A380– 57–8014 Revision 1 * * * • Introduces an optional terminating action [installing reinforced part]. AD 2009–10–07 applies to all Airbus Model A380–841, –842, and –861 airplanes. This AD retains the requirements of AD 2009–10–07. Airplanes were removed from the applicability of AD 2009–10–07 by excluding airplanes on which Airbus modification 68729 is done in production. This AD also revises the compliance time for the inspections of replaced parts. The compliance time is reduced for certain parts and extended for certain other parts, depending on the flight cycles since first installation of the part. The replacement parts must be inspected within the thresholds specified in paragraph (f)(1) of this AD. Relevant Service Information Since we issued AD 2009–10–07, Airbus has issued Mandatory Service Bulletin A380–57–8014, Revision 01, dated June 5, 2009; and Service Bulletin A380–57–8017, dated June 5, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. mstockstill on DSKH9S0YB1PROD with RULES FAA’s Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future. Differences Between the 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 VerDate Nov<24>2008 16:17 Feb 22, 2010 Jkt 220001 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 FAA policies. Any such differences are highlighted in a NOTE within the AD. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0038; Directorate Identifier 2009–NM–110– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. 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 AD. 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. 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. 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15902 (74 FR 22422, May 13, 2009) and adding the following new AD: ■ 2010–04–10 Airbus: Amendment 39–16203. Docket No. FAA–2010–0038; Directorate Identifier 2009–NM–110–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 10, 2010. Affected ADs (b) This AD supersedes AD 2009–10–07, Amendment 39–15902. Applicability (c) This AD applies to Airbus Model A380– 841, –842, and –861 airplanes, certificated in any category, all serial numbers, except airplanes on which Airbus modification 68729 has been done in production. E:\FR\FM\23FER1.SGM 23FER1 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Reason (e) The mandatory continued airworthiness information (MCAI) states: During the flight test campaign of the A380–861 model (Engine Alliance powered), some cracks were found on the Movable Flap Track Fairing number 6 (MFTF#6). These cracks were located at the pivot attachment support-ring and at the U-frame in the attachment area to aft-kinematic. In addition, delamination has been observed within the monolithic Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot support-ring. This condition, if not corrected, could lead to in-flight loss of the MFTF#6, potentially resulting in injuries to persons on the ground. To prevent the risk of a MFTF#6 detachment, EASA AD 2008–0216 required an inspection programme in order to detect cracks before they become critical and in case of findings to replace the MFTF#6. This AD, which supersedes EASA AD 2008–0216: • Cancels the MFTF#6 General Visual Inspection requirement, • Refers to Airbus Service Bulletin A380– 57–8014 Revision 1, * * * • Introduces an optional terminating action. mstockstill on DSKH9S0YB1PROD with RULES Restatement of Requirements of AD 2009– 10–07, With Revised Inspection, Service Information, and Compliance Time for the Inspection of Replaced Parts Actions and Compliance (f) Unless already done, do the following actions. (1) At the applicable time specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD for the left- and right-hand MFTF#6, do a special detailed (ultrasonic and high-frequency eddy current) inspection of the filet radii of pivot supports, monolithic carbon fibre reinforced plastic structures, and radii of the U-frame, for cracking and delamination in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380–57–8014, dated November 21, 2008; or Airbus Mandatory Service Bulletin A380–57–8014, Revision 01, dated June 5, 2009. After the effective date of this AD, use only Revision 01. (i) For Airbus Model A380–841 and –842 airplanes: Before the MFTF#6 has accumulated 500 total flight cycles since its first installation on an airplane, or within 30 flight hours after May 28, 2009 (the effective date of AD 2009–10–07), whichever occurs later. (ii) For Model A380–861 airplanes: Before the MFTF#6 has accumulated 100 total flight cycles since its first installation on an airplane, or within 30 flight hours after May 28, 2009, whichever occurs later. (2) If no cracking and no delamination are found during any inspection required by paragraph (f)(1) of this AD, repeat the inspections required by paragraph (f)(1) of this AD thereafter at intervals not to exceed VerDate Nov<24>2008 16:17 Feb 22, 2010 Jkt 220001 the applicable time specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD. (i) For Model A380–841 and –842 airplanes: 50 flight cycles. (ii) For Model A380–861 airplanes: 10 flight cycles. (3) If any cracking or delamination is found during any inspection required by paragraph (f)(1) or (f)(2) of this AD, before further flight, replace the MFTF#6 with a new or serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380–57–8014, dated November 21, 2008; or Airbus Mandatory Service Bulletin A380–57–8014, Revision 01, dated June 5, 2009. For parts replaced before the effective date of this AD, repeat the inspections specified in paragraph (f)(1) of this AD at the later of the times specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD. For parts replaced on or after the effective date of this AD, repeat the inspections specified in paragraph (f)(1) of this AD at the applicable time defined in paragraph (f)(1) of this AD. After the effective date of this AD, use only Revision 01 for the replacement. (i) At the applicable time defined in paragraph (f)(2) of this AD. (ii) At the applicable time defined in paragraph (f)(1) of this AD. New Requirements of This AD Actions and Compliance (g) Unless already done, do the following actions. (1) In case of MFTF#6 replacement, submit a report using Appendix 01 of Airbus Service Bulletin A380–57–8014, dated November 21, 2008, to Airbus Central Entity, Dept SEES5, 1, Rond Point Maurice Bellonte, 31707 Blagnac, France; e-mail Frederic.molinier@airbus.com; at the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. The report must include the serial number of the removed MFTF#6, the associated airplane manufacturer serial number, and the number of flight cycles accumulated by the MFTF#6 at the time of removal. (i) If the MFTF#6 replacement was done on or after the effective date of this AD: Submit the report within 30 days after the MFTF#6 removal. (ii) If the MFTF#6 replacement was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (2) Replacement of the MFTF#6 with a reinforced MFTF#6, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A380–57–8017, dated June 5, 2009, terminates the requirements 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 (h) 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 7933 approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate 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 (i) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2009–0152, dated July 14, 2009; Airbus Service Bulletin A380– 57–8014, dated November 21, 2008; Airbus Mandatory Service Bulletin A380–57–8014, Revision 01, dated June 5, 2009; and Airbus Service Bulletin A380–57–8017, dated June 5, 2009; for related information. Material Incorporated by Reference (j) You must use Airbus Service Bulletin A380–57–8014, including Appendix 01, dated November 21, 2008; Airbus Mandatory Service Bulletin A380–57–8014, Revision 01, dated June 5, 2009; and Airbus Service Bulletin A380–57–8017, dated June 5, 2009; as applicable; 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 Airbus Mandatory Service Bulletin A380–57– 8014, Revision 01, dated June 5, 2009; and Airbus Service Bulletin A380–57–8017, dated June 5, 2009; under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus Service Bulletin A380– 57–8014, including Appendix 01, dated November 21, 2008, on May 28, 2009 (74 FR 22422, May 13, 2009). (3) For service information identified in this AD, contact Airbus SAS—EANA (Airworthiness Office); 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 562 110 253; Fax +33 562 110 307; e-mail account.airworthA380@airbus.com; Internet https:// www.airbus.com. (4) You may review copies of the service information at the FAA, Transport Airplane E:\FR\FM\23FER1.SGM 23FER1 7934 Federal Register / Vol. 75, No. 35 / Tuesday, February 23, 2010 / Rules and Regulations 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. (5) 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on February 5, 2010. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–3121 Filed 2–22–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0093; Directorate Identifier 97–ANE–06–AD; Amendment 39– 16198; AD 2010–04–05] RIN 2120–AA64 Airworthiness Directives; McCauley Propeller Systems 1A103/TCM Series Propellers mstockstill on DSKH9S0YB1PROD with RULES AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for McCauley Propeller Systems 1A103/ TCM series propellers. That AD requires, for certain serial numbers (S/Ns) of McCauley Propeller Systems 1A103/TCM series propellers, initial and repetitive visual and dye penetrant inspections for cracks in the propeller hub, replacement of propellers with cracks that do not meet acceptable limits, and rework of propellers with cracks that meet acceptable limits. This AD requires, for all McCauley Propeller Systems 1A103/TCM series propellers, the same actions but at reduced compliance times. This AD also requires inspections of the bolt holes, reaming holes if necessary, and inspections of steel reinforcement plates and gaskets. This AD results from 16 reports received of propeller hubs found cracked since AD 2003–12–05 was issued. We are issuing this AD to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the airplane. DATES: Effective March 10, 2010. The Director of the Federal Register VerDate Nov<24>2008 16:17 Feb 22, 2010 Jkt 220001 approved the incorporation by reference of certain publications listed in the regulations as of March 10, 2010. We must receive any comments on this AD by April 26, 2010. ADDRESSES: Use one of the following addresses to comment on this AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: Thomas Teplik, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, Small Airplane Directorate, 1801 Airport Road, Room 100, Wichita, KS 67209; e-mail: thomas.teplik@faa.gov; telephone: (316) 946–4196; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: The FAA amends 14 CFR part 39 by superseding AD 2003–12–05, Amendment 39–13190 (68 FR 35155, June 12, 2003). That AD requires, for certain S/Ns of McCauley Propeller Systems 1A103/TCM series propellers, initial and repetitive visual and dye penetrant inspections for cracks in the propeller hub, replacement of propellers with cracks that do not meet acceptable limits, and rework of propellers with cracks that meet acceptable limits. That AD was the result of reports of hub cracking on the camber (forward) side of the propeller hub near the attachment bolt holes on certain propellers. That condition, if not corrected, could result in propeller separation due to hub fatigue cracking, which can result in loss of control of the airplane. Relevant Service Information We have reviewed and approved the technical contents of McCauley Propeller Systems Alert Service Bulletin (ASB) No. ASB221E, dated January 28, 2010. That ASB describes, for all McCauley Propeller Systems 1A103/ TCM series propellers, procedures for initial and repetitive visual and dye penetrant inspections for cracks in the propeller hub, removal from service of propellers with cracks that do not meet acceptable limits, and rework of propellers with cracks that meet acceptable limits. Actions Since AD 2003–12–05 Was Issued Interim Action These actions are interim actions and we may take further rulemaking actions in the future. Since AD 2003–12–05 was issued, we received 16 reports of propeller hubs found cracked. Two of the cracks were on propellers outside the propeller range of serial numbers affected by AD 2003–12–05. These cracks began at a bolt hole and extended through to the hub outer surface. These propellers had fewer than 3,000 operating hours timein-service (TIS). AD 2003–12–05 required inspections starting at 3,000 operating hours TIS. We have not yet been able to determine the cause of the propeller hub cracking. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other McCauley Propeller Systems 1A103/TCM series propellers of the same type design. We are issuing this AD to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the airplane. This AD requires, for all McCauley Propeller Systems 1A103/TCM series propellers, initial and repetitive visual and dye penetrant inspections for cracks in the propeller hub, including bolt holes, reaming holes if necessary, inspections of steel reinforcement plates and gaskets, removal from service of propellers with cracks that do not meet acceptable limits, and rework of propellers with cracks that meet acceptable limits. You must use the service information described previously to perform the actions required by this AD. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2010–0093; Directorate Identifier 97– E:\FR\FM\23FER1.SGM 23FER1

Agencies

[Federal Register Volume 75, Number 35 (Tuesday, February 23, 2010)]
[Rules and Regulations]
[Pages 7931-7934]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-3121]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0038; Directorate Identifier 2009-NM-110-AD; 
Amendment 39-16203; AD 2010-04-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A380-841, -842, and -861 
Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is 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:

    During the flight test campaign of the A380-861 model (Engine 
Alliance powered), some cracks were found on the Movable Flap Track 
Fairing number 6 (MFTF6).
    These cracks were located at the pivot attachment support-ring 
and at the U-frame in the attachment area to aft-kinematic. In 
addition, delamination has been observed within the monolithic 
Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot 
support-ring.
    This condition, if not corrected, could lead to in-flight loss 
of the MFTF6, potentially resulting in injuries to persons 
on the ground.
* * * * *
This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

DATES: This AD becomes effective March 10, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 10, 
2010.
    On May 28, 2009 (74 FR 22422, May 13, 2009), the Director of the 
Federal Register approved the incorporation by reference of a certain 
other publication listed in the AD.
    We must receive comments on this AD by April 9, 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.

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 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: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    On May 1, 2009, the FAA issued AD 2009-10-07, Amendment 39-15902 
(74 FR 22422, May 13, 2009). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued that AD, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2009-0152, 
dated July 14, 2009 (referred to after this as ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    During the flight test campaign of the A380-861 model (Engine 
Alliance powered), some cracks were found on the Movable Flap Track 
Fairing number 6 (MFTF6).
    These cracks were located at the pivot attachment support-ring 
and at the U-frame in the attachment area to aft-kinematic. In 
addition, delamination has been observed within the monolithic 
Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot 
support-ring.
    This condition, if not corrected, could lead to in-flight loss 
of the MFTF6, potentially resulting in injuries to persons 
on the ground.
    To prevent the risk of a MFTF6 detachment, EASA AD 
2008-0216 (which corresponds to FAA AD 2009-10-07) required an 
inspection programme in order to

[[Page 7932]]

detect cracks before they become critical and in case of findings to 
replace the MFTF6.
    This AD, which supersedes EASA AD 2008-0216:
     Cancels the MFTF6 General Visual Inspection 
requirement,
     Refers to Airbus Service Bulletin A380-57-8014 Revision 
1 * * *
     Introduces an optional terminating action [installing 
reinforced part].

    AD 2009-10-07 applies to all Airbus Model A380-841, -842, and -861 
airplanes. This AD retains the requirements of AD 2009-10-07. Airplanes 
were removed from the applicability of AD 2009-10-07 by excluding 
airplanes on which Airbus modification 68729 is done in production. 
This AD also revises the compliance time for the inspections of 
replaced parts. The compliance time is reduced for certain parts and 
extended for certain other parts, depending on the flight cycles since 
first installation of the part. The replacement parts must be inspected 
within the thresholds specified in paragraph (f)(1) of this AD.

Relevant Service Information

    Since we issued AD 2009-10-07, Airbus has issued Mandatory Service 
Bulletin A380-57-8014, Revision 01, dated June 5, 2009; and Service 
Bulletin A380-57-8017, dated June 5, 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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    There are no products of this type currently registered in the 
United States. However, this rule is necessary to ensure that the 
described unsafe condition is addressed if any of these products are 
placed on the U.S. Register in the future.

Differences Between the 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 FAA policies. Any such differences are 
highlighted in a NOTE within the AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2010-0038; Directorate 
Identifier 2009-NM-110-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    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 AD.

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.

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 39-15902 (74 FR 
22422, May 13, 2009) and adding the following new AD:

2010-04-10 Airbus: Amendment 39-16203. Docket No. FAA-2010-0038; 
Directorate Identifier 2009-NM-110-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
10, 2010.

Affected ADs

    (b) This AD supersedes AD 2009-10-07, Amendment 39-15902.

Applicability

    (c) This AD applies to Airbus Model A380-841, -842, and -861 
airplanes, certificated in any category, all serial numbers, except 
airplanes on which Airbus modification 68729 has been done in 
production.

[[Page 7933]]

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:
    During the flight test campaign of the A380-861 model (Engine 
Alliance powered), some cracks were found on the Movable Flap Track 
Fairing number 6 (MFTF6).
    These cracks were located at the pivot attachment support-ring 
and at the U-frame in the attachment area to aft-kinematic. In 
addition, delamination has been observed within the monolithic 
Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot 
support-ring.
    This condition, if not corrected, could lead to in-flight loss 
of the MFTF6, potentially resulting in injuries to persons 
on the ground.
    To prevent the risk of a MFTF6 detachment, EASA AD 
2008-0216 required an inspection programme in order to detect cracks 
before they become critical and in case of findings to replace the 
MFTF6.
    This AD, which supersedes EASA AD 2008-0216:
     Cancels the MFTF6 General Visual Inspection 
requirement,
     Refers to Airbus Service Bulletin A380-57-8014 Revision 
1, * * *
     Introduces an optional terminating action.

Restatement of Requirements of AD 2009-10-07, With Revised Inspection, 
Service Information, and Compliance Time for the Inspection of Replaced 
Parts

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) At the applicable time specified in paragraph (f)(1)(i) or 
(f)(1)(ii) of this AD for the left- and right-hand MFTF6, 
do a special detailed (ultrasonic and high-frequency eddy current) 
inspection of the filet radii of pivot supports, monolithic carbon 
fibre reinforced plastic structures, and radii of the U-frame, for 
cracking and delamination in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A380-57-8014, dated November 
21, 2008; or Airbus Mandatory Service Bulletin A380-57-8014, 
Revision 01, dated June 5, 2009. After the effective date of this 
AD, use only Revision 01.
    (i) For Airbus Model A380-841 and -842 airplanes: Before the 
MFTF6 has accumulated 500 total flight cycles since its 
first installation on an airplane, or within 30 flight hours after 
May 28, 2009 (the effective date of AD 2009-10-07), whichever occurs 
later.
    (ii) For Model A380-861 airplanes: Before the MFTF6 has 
accumulated 100 total flight cycles since its first installation on 
an airplane, or within 30 flight hours after May 28, 2009, whichever 
occurs later.
    (2) If no cracking and no delamination are found during any 
inspection required by paragraph (f)(1) of this AD, repeat the 
inspections required by paragraph (f)(1) of this AD thereafter at 
intervals not to exceed the applicable time specified in paragraph 
(f)(2)(i) or (f)(2)(ii) of this AD.
    (i) For Model A380-841 and -842 airplanes: 50 flight cycles.
    (ii) For Model A380-861 airplanes: 10 flight cycles.
    (3) If any cracking or delamination is found during any 
inspection required by paragraph (f)(1) or (f)(2) of this AD, before 
further flight, replace the MFTF6 with a new or serviceable 
part, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A380-57-8014, dated November 21, 2008; or Airbus 
Mandatory Service Bulletin A380-57-8014, Revision 01, dated June 5, 
2009. For parts replaced before the effective date of this AD, 
repeat the inspections specified in paragraph (f)(1) of this AD at 
the later of the times specified in paragraphs (f)(3)(i) and 
(f)(3)(ii) of this AD. For parts replaced on or after the effective 
date of this AD, repeat the inspections specified in paragraph 
(f)(1) of this AD at the applicable time defined in paragraph (f)(1) 
of this AD. After the effective date of this AD, use only Revision 
01 for the replacement.
    (i) At the applicable time defined in paragraph (f)(2) of this 
AD.
    (ii) At the applicable time defined in paragraph (f)(1) of this 
AD.

New Requirements of This AD

Actions and Compliance

    (g) Unless already done, do the following actions.
    (1) In case of MFTF6 replacement, submit a report using 
Appendix 01 of Airbus Service Bulletin A380-57-8014, dated November 
21, 2008, to Airbus Central Entity, Dept SEES5, 1, Rond Point 
Maurice Bellonte, 31707 Blagnac, France; e-mail 
Frederic.molinier@airbus.com; at the applicable time specified in 
paragraph (g)(1)(i) or (g)(1)(ii) of this AD. The report must 
include the serial number of the removed MFTF6, the 
associated airplane manufacturer serial number, and the number of 
flight cycles accumulated by the MFTF6 at the time of 
removal.
    (i) If the MFTF6 replacement was done on or after the 
effective date of this AD: Submit the report within 30 days after 
the MFTF6 removal.
    (ii) If the MFTF6 replacement was done before the 
effective date of this AD: Submit the report within 30 days after 
the effective date of this AD.
    (2) Replacement of the MFTF6 with a reinforced 
MFTF6, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A380-57-8017, dated June 5, 2009, 
terminates the requirements 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

    (h) 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: Todd 
Thompson, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate 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

    (i) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2009-0152, dated July 14, 2009; 
Airbus Service Bulletin A380-57-8014, dated November 21, 2008; 
Airbus Mandatory Service Bulletin A380-57-8014, Revision 01, dated 
June 5, 2009; and Airbus Service Bulletin A380-57-8017, dated June 
5, 2009; for related information.

Material Incorporated by Reference

    (j) You must use Airbus Service Bulletin A380-57-8014, including 
Appendix 01, dated November 21, 2008; Airbus Mandatory Service 
Bulletin A380-57-8014, Revision 01, dated June 5, 2009; and Airbus 
Service Bulletin A380-57-8017, dated June 5, 2009; as applicable; 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 Airbus Mandatory Service Bulletin 
A380-57-8014, Revision 01, dated June 5, 2009; and Airbus Service 
Bulletin A380-57-8017, dated June 5, 2009; under 5 U.S.C. 552(a) and 
1 CFR part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Airbus Service Bulletin A380-57-8014, 
including Appendix 01, dated November 21, 2008, on May 28, 2009 (74 
FR 22422, May 13, 2009).
    (3) For service information identified in this AD, contact 
Airbus SAS--EANA (Airworthiness Office); 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 562 110 253; 
Fax +33 562 110 307; e-mail account.airworth-A380@airbus.com; 
Internet https://www.airbus.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane

[[Page 7934]]

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.
    (5) 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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on February 5, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-3121 Filed 2-22-10; 8:45 am]
BILLING CODE 4910-13-P
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