Airworthiness Directives; Airbus Airplanes, 68711-68714 [2012-27847]

Download as PDF Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules Dated: September 21, 2012. John Charles Padalino, Acting Administrator, Rural Utilities Service. [FR Doc. 2012–27631 Filed 11–15–12; 8:45 am] BILLING CODE P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1163; Directorate Identifier 2011–NM–246–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A330– 200 and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. The existing AD currently requires a one-time detailed inspection of both main landing gear (MLG) bogie beams in the region of the bogie stop pad for detection of deformation and damage, and corrective actions if necessary. Since we issued that AD, we have received reports of corroded bogie stop pads, including some with cracking. This proposed AD would add Model A330–200 Freighter series airplanes to the applicability. For certain airplanes, this proposed AD would also add repetitive inspections for damage and corrosion of the sliding piston sub-assembly, with new related investigative and corrective actions. We are proposing this AD to detect and correct deformation or damage under the bogie stop pad of both MLG bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane or collapse of the MLG and departure of the airplane from the runway. DATES: We must receive comments on this proposed AD by December 31, 2012. 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. emcdonald on DSK7TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 15:42 Nov 15, 2012 Jkt 229001 • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 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— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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, WA. 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; 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–2012–1163; Directorate Identifier 2011–NM–246–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to 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. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 68711 Discussion On January 14, 2010, we issued AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). That AD required actions intended to address an unsafe condition on Airbus Model A330–200 and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. Since we issued AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2011–0211, dated October 31, 2011 (referred to after this as ‘‘the MCAI’’), to supersede EASA AD 2008–0223, dated December 15, 2008 (referred to in the existing AD), and correct an unsafe condition for the specified products. The MCAI states: During a scheduled maintenance inspection on the MLG [main landing gear], the bogie stop pad was found deformed and cracked. Upon removal of the bogie stop pad for replacement, the bogie beam was also found cracked. Laboratory investigation indicates that an overload event has occurred and no fatigue propagation of the crack was evident. A second bogie beam crack has subsequently been found on another aeroplane, located under a bogie stop pad which only had superficial paint damage. This condition, if not detected and corrected, could result in the aeroplane departing the runway or to the bogie detaching from the areoplane or gear collapses, which would all constitute unsafe conditions at speeds above 30 knots. As a precautionary measure, EASA AD 2008–0223 [which corresponds to FAA AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010] required one-time detailed inspections under the bogie stop pad of both MLG bogie beams and, in case deformation or damage is detected, to apply the associated repair. Numerous bogie stop pad were found corroded and a few cracked as a result of the one-time inspection required by EASA AD 2008–0223 on A330, A340–200, and A340– 300 aeroplanes. For the reasons describe above, this [EASA] AD, which supersedes EASA AD 2008–0223: —Retains the initial inspection requirement of EASA AD 2008–0223 for A330, A340– 200, and A340–300 aeroplanes. —Introduces a repetitive detailed visual inspection for A330, A340–200, and A340– 300 aeroplanes. —Retains the requirement of EASA AD 2008–0223 for A340–500 and A340–600 aeroplanes, for which further mandatory requirements might follow in future mandatory requirements might follow in future depending on the results of the onetime mandatory inspection in place. The required actions include repetitive detailed inspections for E:\FR\FM\16NOP1.SGM 16NOP1 68712 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules damage and corrosion of the sliding piston sub-assembly, with new related investigative and corrective actions. Related investigative actions include a test for indications of corrosion and damage to the bogie assembly base material, and a magnetic particle inspection for cracks, corrosion, and damage of the bogie beam. Corrective actions include repairing affected parts. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued the following service bulletins: • Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011 (for Model A330–200 and –300 series airplanes). • Airbus Mandatory Service Bulletin A330–32–3248, including Appendix 1, dated October 5, 2011 (for Model A330– 200, –200 Freighter, and –300 series airplanes). • Airbus Mandatory Service Bulletin A340–32–4286, including Appendix 1, dated October 5, 2011 (for Model A340– 200 and –300 series airplanes). 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. emcdonald on DSK7TPTVN1PROD with PROPOSALS Differences Between Proposed AD and Service Information Although the service information specifies to contact the manufacturer for instructions to repair certain conditions, this proposed AD would require repairing those conditions using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent). Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 67 products of U.S. registry. VerDate Mar<15>2010 15:42 Nov 15, 2012 Jkt 229001 The actions that are required by AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), and retained in this proposed AD take about 2 workhours per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the currently required actions is $170 per product. We estimate that it would take about 16 work-hours per product to comply with the new 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 $91,120, or $1,360 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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. 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. 1. The authority citation for part 39 continues to read as follows: 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); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), and adding the following new AD: Airbus: Docket No. FAA–2012–1163; Directorate Identifier 2011–NM–246–AD. (a) Comments Due Date We must receive comments by December 31, 2012. (b) Affected ADs This AD supersedes AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). (c) Applicability This AD applies to all Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 series airplanes; and Model A340–211, –212, –213, –311, –312, –313 series airplanes; and A340–541 and –642 airplanes; certificated in any category; all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 32: Landing gear. (e) Reason This AD was prompted by reports of corroded bogie stop pads, some with cracking. We are issuing this AD to detect and correct deformation or damage under the bogie stop pad of both main landing gear (MLG) bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane or collapse of the MLG and departure of the airplane from the runway. (f) Compliance You are responsible for having the actions required by this AD performed within the E:\FR\FM\16NOP1.SGM 16NOP1 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules emcdonald on DSK7TPTVN1PROD with PROPOSALS compliance times specified, unless the actions have already been done. (g) Retained One-Time Inspection and Corrective Actions, With Revised Service Information This paragraph restates the requirements of paragraph (f)(1) of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), with revised service information. For Model A330–200 and –300 series airplanes, and Model A340–200, –300, –500, and –600 series airplanes, except as required by paragraph (i) of this AD: At the applicable compliance time specified in paragraph (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), or (g)(6) of this AD, perform one-time detailed inspections of both MLG bogie beams in the region of the bogie stop pad for detection of deformation and damage, and apply the applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (g)(7) of this AD. Do all applicable corrective actions before further flight. (1) Airplanes with 22 months or less and 2,500 flight cycles or less from the first flight with the original bogie beam as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months on the original bogie beam, whichever occurs first, but not later than 40 months from first flight. (2) Airplanes with 22 months or less and 2,500 flight cycles or less from the installation date of a new bogie beam in service as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months from the installation date of the new bogie beam, whichever occurs first, but not later than 40 months from the installation date of a new bogie beam in service. (3) Airplanes with 22 months or less and 2,500 flight cycles or less from the installation date of an overhauled bogie beam in service as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months from the installation date of the overhauled bogie beam in service, whichever occurs first, but not later than 40 months from the installation date of the overhauled bogie beam in service. (4) Airplanes with more than 22 months or more than 2,500 flight cycles from the first flight with the original bogie beam, as of March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010– 02–10). (5) Airplanes with more than 22 months or more than 2,500 flight cycles from the installation date of a new bogie beam in service, as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010–02–10). (6) Airplanes with more than 22 months or more than 2,500 flight cycles from the installation date of an overhauled bogie beam VerDate Mar<15>2010 15:42 Nov 15, 2012 Jkt 229001 68713 in service, as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010–02–10). (7) Use the applicable service information to accomplish the actions required by paragraph (g) of this AD. (i) For Model A330–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008; or Airbus Mandatory Service Bulletin A330–32– 3220, Revision 01, dated October 5, 2011. (ii) For Model A340–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (iii) For Model A340–500 and –600 series airplanes: Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. airplane after its most recent overhaul, but not later than 40 months since its first flight on an airplane after its most recent overhaul. (2) Within 90 days after the effective date of this AD. (3) Use the applicable service information specified in paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD, to accomplish the actions required by paragraph (i) of this AD. (i) For Model A330–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011. (ii) For Model A340–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (iii) For Model A340–500 and –600 series airplanes: Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. (h) Retained Reporting Requirement This paragraph restates the requirements of paragraph (f)(2) of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). Report the results of the inspection required by paragraph (g) of this AD, including no findings, to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical Data and Documentation Services; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) If the inspection is done on or after March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Submit the report within 30 days after doing the inspection. (2) If the inspection was done prior to March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Submit the report within 30 days after March 4, 2010 (the effective date of AD 2010–02–10). (j) New Repetitive Inspections Except for bogie beams that have been inspected as specified in Airbus Mandatory Service Bulletin A340–32–5087: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, do the detailed inspection of both MLG bogie beams in the bogie stop pad area for damage and corrosion, and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32–3248, dated October 5, 2011 (for Model A330–200, –200 Freighter, and –300 series airplanes); or Airbus Mandatory Service Bulletin A340–32– 4286, dated October 5, 2011 (for Model A340–200 and –300 series airplanes); except as required by paragraph (k) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 2,500 flight cycles or 24 months, whichever is first. (1) Within 2,500 flight cycles or 24 months, whichever occurs first, accumulated by a MLG bogie beam since its first flight after the most recent accomplishment of Airbus Mandatory Service Bulletin A330–32–3220 or A340–32–4264, as applicable. (2) Within 3 months after the effective date of this AD. (i) New Inspections of Beams That Have Not Been Inspected as of the Effective Date of This AD For bogie beams on which the inspection required by paragraph (g) of this AD has not been accomplished as of the effective date of this AD: At the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, perform one-time detailed inspections of both main landing gear bogie beams in the region of the bogie stop pad for detection of deformation and damage, and apply the applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. (1) At the applicable time in paragraph (i)(1)(i) or (i)(1)(ii) of this AD. (i) For bogie beams that have not been overhauled: Not earlier than 2,500 flight cycles or 22 months, whichever occurs first, on a bogie beam since its first flight on an airplane since new, but not later than 40 months since its first flight on an airplane since new. (ii) For bogie beams that have been overhauled: Not earlier than 2,500 flight cycles or 22 months, whichever occurs first, on a bogie beam since its first flight on an PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 (k) Service Information Exception If any cracking of the bogie beam is detected during any inspection or repair required by paragraph (j) of this AD, or any repair required by paragraph (j) of this AD is beyond the maximum repair allowance specified in the service information required by paragraph (j) of this AD: Before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). (l) New Reporting Requirement Report the results of the initial inspection required by paragraph (j) of this AD, including both positive and negative findings, to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical Data and Documentation Services; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com at the applicable E:\FR\FM\16NOP1.SGM 16NOP1 68714 Federal Register / Vol. 77, No. 222 / Friday, November 16, 2012 / Proposed Rules time specified in paragraph (l)(1) or (1)(2) of this AD. (1) If the inspection is done on or after the effective date of this AD: Submit the report within 30 days after doing the inspection. (2) If the inspection was done prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. emcdonald on DSK7TPTVN1PROD with PROPOSALS (m) Other FAA AD Provisions 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1138; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), are approved as AMOCs for the corresponding provisions of 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: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing, and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. VerDate Mar<15>2010 15:42 Nov 15, 2012 Jkt 229001 (n) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed if any crack is found during any inspection required by this AD. (o) Related Information (1) Refer to MCAI EASA Airworthiness Directive 2011–0211, dated October 1, 2011, and the service information specified in paragraphs (o)(1)(i) through (o)(1)(vi) of this AD, for related information. (i) Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008. (ii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011. (iii) Airbus Mandatory Service Bulletin A330–32–3248, dated October 5, 2011. (iv) Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (v) Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011. (vi) Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. (2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on November 8, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–27847 Filed 11–15–12; 8:45 am] BILLING CODE 4910–13–P proposed AD was prompted by RRD performing an evaluation that determined that certain high-pressure turbine (HPT) stage 1 and stage 2 discs from a specific supplier may contain steel inclusions that may cause the discs to fail before they reach their current life limits. This proposed AD would require reducing the life limits for certain HPT stage 1 and stage 2 discs. We are proposing this AD to prevent failure of the HPT stage 1 and stage 2 discs, which could result in uncontained failure of the engine and damage to the airplane. DATES: We must receive comments on this proposed AD by January 15, 2013. ADDRESSES: You may send comments by any of the following methods: • 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 service information identified in this proposed AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49 0 33– 7086–1883; fax: 49 0 33–7086–3276. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration 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 (phone: 800–647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7154; fax: 781–238– 7199; email: robert.c.morlath@faa.gov. 14 CFR Part 39 [Docket No. FAA–2012–1055; Directorate Identifier 2012–NE–33–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700–710A1–10 and BR700– 710A2–20 turbofan engines, and certain BR700–710C4–11 model engines. This SUMMARY: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\16NOP1.SGM 16NOP1

Agencies

[Federal Register Volume 77, Number 222 (Friday, November 16, 2012)]
[Proposed Rules]
[Pages 68711-68714]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27847]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1163; Directorate Identifier 2011-NM-246-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to all Airbus Model A330-200 and -300 series 
airplanes; and Model A340-200, -300, -500, and -600 series airplanes. 
The existing AD currently requires a one-time detailed inspection of 
both main landing gear (MLG) bogie beams in the region of the bogie 
stop pad for detection of deformation and damage, and corrective 
actions if necessary. Since we issued that AD, we have received reports 
of corroded bogie stop pads, including some with cracking. This 
proposed AD would add Model A330-200 Freighter series airplanes to the 
applicability. For certain airplanes, this proposed AD would also add 
repetitive inspections for damage and corrosion of the sliding piston 
sub-assembly, with new related investigative and corrective actions. We 
are proposing this AD to detect and correct deformation or damage under 
the bogie stop pad of both MLG bogie beams, which could result in a 
damaged bogie beam and consequent detachment of the beam from the 
airplane or collapse of the MLG and departure of the airplane from the 
runway.

DATES: We must receive comments on this proposed AD by December 31, 
2012.

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 W12-140, 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--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@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, WA. 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; 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-2012-1163; 
Directorate Identifier 2011-NM-246-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to 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

    On January 14, 2010, we issued AD 2010-02-10, Amendment 39-16181 
(75 FR 4477, January 28, 2010). That AD required actions intended to 
address an unsafe condition on Airbus Model A330-200 and -300 series 
airplanes; and Model A340-200, -300, -500, and -600 series airplanes.
    Since we issued AD 2010-02-10, Amendment 39-16181 (75 FR 4477, 
January 28, 2010), the European Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2011-0211, dated October 31, 
2011 (referred to after this as ``the MCAI''), to supersede EASA AD 
2008-0223, dated December 15, 2008 (referred to in the existing AD), 
and correct an unsafe condition for the specified products. The MCAI 
states:

    During a scheduled maintenance inspection on the MLG [main 
landing gear], the bogie stop pad was found deformed and cracked. 
Upon removal of the bogie stop pad for replacement, the bogie beam 
was also found cracked.
    Laboratory investigation indicates that an overload event has 
occurred and no fatigue propagation of the crack was evident.
    A second bogie beam crack has subsequently been found on another 
aeroplane, located under a bogie stop pad which only had superficial 
paint damage.
    This condition, if not detected and corrected, could result in 
the aeroplane departing the runway or to the bogie detaching from 
the areoplane or gear collapses, which would all constitute unsafe 
conditions at speeds above 30 knots.
    As a precautionary measure, EASA AD 2008-0223 [which corresponds 
to FAA AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 
2010] required one-time detailed inspections under the bogie stop 
pad of both MLG bogie beams and, in case deformation or damage is 
detected, to apply the associated repair.
    Numerous bogie stop pad were found corroded and a few cracked as 
a result of the one-time inspection required by EASA AD 2008-0223 on 
A330, A340-200, and A340-300 aeroplanes.
    For the reasons describe above, this [EASA] AD, which supersedes 
EASA AD 2008-0223:
--Retains the initial inspection requirement of EASA AD 2008-0223 
for A330, A340-200, and A340-300 aeroplanes.
--Introduces a repetitive detailed visual inspection for A330, A340-
200, and A340-300 aeroplanes.
--Retains the requirement of EASA AD 2008-0223 for A340-500 and 
A340-600 aeroplanes, for which further mandatory requirements might 
follow in future mandatory requirements might follow in future 
depending on the results of the one-time mandatory inspection in 
place.

    The required actions include repetitive detailed inspections for

[[Page 68712]]

damage and corrosion of the sliding piston sub-assembly, with new 
related investigative and corrective actions. Related investigative 
actions include a test for indications of corrosion and damage to the 
bogie assembly base material, and a magnetic particle inspection for 
cracks, corrosion, and damage of the bogie beam. Corrective actions 
include repairing affected parts.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued the following service bulletins:
     Airbus Mandatory Service Bulletin A330-32-3220, Revision 
01, dated October 5, 2011 (for Model A330-200 and -300 series 
airplanes).
     Airbus Mandatory Service Bulletin A330-32-3248, including 
Appendix 1, dated October 5, 2011 (for Model A330-200, -200 Freighter, 
and -300 series airplanes).
     Airbus Mandatory Service Bulletin A340-32-4286, including 
Appendix 1, dated October 5, 2011 (for Model A340-200 and -300 series 
airplanes).
    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 Proposed AD and Service Information

    Although the service information specifies to contact the 
manufacturer for instructions to repair certain conditions, this 
proposed AD would require repairing those conditions using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA (or its delegated agent).

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 67 products of U.S. registry.
    The actions that are required by AD 2010-02-10, Amendment 39-16181 
(75 FR 4477, January 28, 2010), and retained in this proposed AD take 
about 2 work-hours per product, at an average labor rate of $85 per 
work hour. Based on these figures, the estimated cost of the currently 
required actions is $170 per product.
    We estimate that it would take about 16 work-hours per product to 
comply with the new 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 $91,120, or $1,360 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 removing airworthiness directive 
(AD) 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010), and 
adding the following new AD:

Airbus: Docket No. FAA-2012-1163; Directorate Identifier 2011-NM-
246-AD.

(a) Comments Due Date

    We must receive comments by December 31, 2012.

(b) Affected ADs

    This AD supersedes AD 2010-02-10, Amendment 39-16181 (75 FR 
4477, January 28, 2010).

(c) Applicability

    This AD applies to all Airbus Model A330-201, -202, -203, -223, 
-223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 series airplanes; and Model A340-211, -212, -213, -311, -
312, -313 series airplanes; and A340-541 and -642 airplanes; 
certificated in any category; all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 32: Landing 
gear.

(e) Reason

    This AD was prompted by reports of corroded bogie stop pads, 
some with cracking. We are issuing this AD to detect and correct 
deformation or damage under the bogie stop pad of both main landing 
gear (MLG) bogie beams, which could result in a damaged bogie beam 
and consequent detachment of the beam from the airplane or collapse 
of the MLG and departure of the airplane from the runway.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the

[[Page 68713]]

compliance times specified, unless the actions have already been 
done.

(g) Retained One-Time Inspection and Corrective Actions, With Revised 
Service Information

    This paragraph restates the requirements of paragraph (f)(1) of 
AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010), 
with revised service information. For Model A330-200 and -300 series 
airplanes, and Model A340-200, -300, -500, and -600 series 
airplanes, except as required by paragraph (i) of this AD: At the 
applicable compliance time specified in paragraph (g)(1), (g)(2), 
(g)(3), (g)(4), (g)(5), or (g)(6) of this AD, perform one-time 
detailed inspections of both MLG bogie beams in the region of the 
bogie stop pad for detection of deformation and damage, and apply 
the applicable corrective actions, in accordance with the 
Accomplishment Instructions of the applicable service bulletin 
specified in paragraph (g)(7) of this AD. Do all applicable 
corrective actions before further flight.
    (1) Airplanes with 22 months or less and 2,500 flight cycles or 
less from the first flight with the original bogie beam as of March 
4, 2010 (the effective date of AD 2010-02-10, Amendment 39-16181 (75 
FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 
22 months on the original bogie beam, whichever occurs first, but 
not later than 40 months from first flight.
    (2) Airplanes with 22 months or less and 2,500 flight cycles or 
less from the installation date of a new bogie beam in service as of 
March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight 
cycles or 22 months from the installation date of the new bogie 
beam, whichever occurs first, but not later than 40 months from the 
installation date of a new bogie beam in service.
    (3) Airplanes with 22 months or less and 2,500 flight cycles or 
less from the installation date of an overhauled bogie beam in 
service as of March 4, 2010 (the effective date of AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010)): Not earlier than 
2,500 flight cycles or 22 months from the installation date of the 
overhauled bogie beam in service, whichever occurs first, but not 
later than 40 months from the installation date of the overhauled 
bogie beam in service.
    (4) Airplanes with more than 22 months or more than 2,500 flight 
cycles from the first flight with the original bogie beam, as of 
March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 
4, 2010 (the effective date of AD 2010-02-10).
    (5) Airplanes with more than 22 months or more than 2,500 flight 
cycles from the installation date of a new bogie beam in service, as 
of March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 
4, 2010 (the effective date of AD 2010-02-10).
    (6) Airplanes with more than 22 months or more than 2,500 flight 
cycles from the installation date of an overhauled bogie beam in 
service, as of March 4, 2010 (the effective date of AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010)): Within 18 months 
after March 4, 2010 (the effective date of AD 2010-02-10).
    (7) Use the applicable service information to accomplish the 
actions required by paragraph (g) of this AD.
    (i) For Model A330-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A330-32-3220, dated October 10, 2008; or 
Airbus Mandatory Service Bulletin A330-32-3220, Revision 01, dated 
October 5, 2011.
    (ii) For Model A340-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-4264, dated October 10, 2008.
    (iii) For Model A340-500 and -600 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-5087, dated October 10, 2008.

(h) Retained Reporting Requirement

    This paragraph restates the requirements of paragraph (f)(2) of 
AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010). 
Report the results of the inspection required by paragraph (g) of 
this AD, including no findings, to Airbus, Customer Services 
Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex 
France; Attn: SEDCC1 Technical Data and Documentation Services; fax 
(+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the 
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) If the inspection is done on or after March 4, 2010 (the 
effective date of AD 2010-02-10, Amendment 39-16181 (75 FR 4477, 
January 28, 2010)): Submit the report within 30 days after doing the 
inspection.
    (2) If the inspection was done prior to March 4, 2010 (the 
effective date of AD 2010-02-10, Amendment 39-16181 (75 FR 4477, 
January 28, 2010)): Submit the report within 30 days after March 4, 
2010 (the effective date of AD 2010-02-10).

(i) New Inspections of Beams That Have Not Been Inspected as of the 
Effective Date of This AD

    For bogie beams on which the inspection required by paragraph 
(g) of this AD has not been accomplished as of the effective date of 
this AD: At the later of the times specified in paragraphs (i)(1) 
and (i)(2) of this AD, perform one-time detailed inspections of both 
main landing gear bogie beams in the region of the bogie stop pad 
for detection of deformation and damage, and apply the applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraph (i)(3) of this AD. Do all applicable corrective actions 
before further flight.
    (1) At the applicable time in paragraph (i)(1)(i) or (i)(1)(ii) 
of this AD.
    (i) For bogie beams that have not been overhauled: Not earlier 
than 2,500 flight cycles or 22 months, whichever occurs first, on a 
bogie beam since its first flight on an airplane since new, but not 
later than 40 months since its first flight on an airplane since 
new.
    (ii) For bogie beams that have been overhauled: Not earlier than 
2,500 flight cycles or 22 months, whichever occurs first, on a bogie 
beam since its first flight on an airplane after its most recent 
overhaul, but not later than 40 months since its first flight on an 
airplane after its most recent overhaul.
    (2) Within 90 days after the effective date of this AD.
    (3) Use the applicable service information specified in 
paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD, to 
accomplish the actions required by paragraph (i) of this AD.
    (i) For Model A330-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A330-32-3220, Revision 01, dated October 
5, 2011.
    (ii) For Model A340-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-4264, dated October 10, 2008.
    (iii) For Model A340-500 and -600 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-5087, dated October 10, 2008.

(j) New Repetitive Inspections

    Except for bogie beams that have been inspected as specified in 
Airbus Mandatory Service Bulletin A340-32-5087: At the later of the 
times specified in paragraphs (j)(1) and (j)(2) of this AD, do the 
detailed inspection of both MLG bogie beams in the bogie stop pad 
area for damage and corrosion, and all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-32-3248, dated October 5, 2011 (for Model A330-200, -200 
Freighter, and -300 series airplanes); or Airbus Mandatory Service 
Bulletin A340-32-4286, dated October 5, 2011 (for Model A340-200 and 
-300 series airplanes); except as required by paragraph (k) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight. Repeat the inspection thereafter at intervals 
not to exceed 2,500 flight cycles or 24 months, whichever is first.
    (1) Within 2,500 flight cycles or 24 months, whichever occurs 
first, accumulated by a MLG bogie beam since its first flight after 
the most recent accomplishment of Airbus Mandatory Service Bulletin 
A330-32-3220 or A340-32-4264, as applicable.
    (2) Within 3 months after the effective date of this AD.

(k) Service Information Exception

    If any cracking of the bogie beam is detected during any 
inspection or repair required by paragraph (j) of this AD, or any 
repair required by paragraph (j) of this AD is beyond the maximum 
repair allowance specified in the service information required by 
paragraph (j) of this AD: Before further flight, repair using a 
method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA) (or its delegated agent).

(l) New Reporting Requirement

    Report the results of the initial inspection required by 
paragraph (j) of this AD, including both positive and negative 
findings, to Airbus, Customer Services Directorate, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical 
Data and Documentation Services; fax (+33) 5 61 93 28 06; email 
sb.reporting@airbus.com at the applicable

[[Page 68714]]

time specified in paragraph (l)(1) or (1)(2) of this AD.
    (1) If the inspection is done on or after the effective date of 
this AD: Submit the report within 30 days after doing the 
inspection.
    (2) If the inspection was done prior to the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(m) Other FAA AD Provisions

    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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD. AMOCs approved previously in accordance with AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010), are approved as 
AMOCs for the corresponding provisions of 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: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing, and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(n) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed if any crack is found during any 
inspection required by this AD.

(o) Related Information

    (1) Refer to MCAI EASA Airworthiness Directive 2011-0211, dated 
October 1, 2011, and the service information specified in paragraphs 
(o)(1)(i) through (o)(1)(vi) of this AD, for related information.
    (i) Airbus Mandatory Service Bulletin A330-32-3220, dated 
October 10, 2008.
    (ii) Airbus Mandatory Service Bulletin A330-32-3220, Revision 
01, dated October 5, 2011.
    (iii) Airbus Mandatory Service Bulletin A330-32-3248, dated 
October 5, 2011.
    (iv) Airbus Mandatory Service Bulletin A340-32-4264, dated 
October 10, 2008.
    (v) Airbus Mandatory Service Bulletin A340-32-4286, dated 
October 5, 2011.
    (vi) Airbus Mandatory Service Bulletin A340-32-5087, dated 
October 10, 2008.
    (2) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@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, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on November 8, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-27847 Filed 11-15-12; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.