Airworthiness Directives; Airbus Airplanes, 13925-13929 [2014-05434]

Download as PDF Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules 1. A Description of the Reasons Action by the Agency Is Being Considered This proposed AD was prompted by failure reports of multiple cylinder head-to-barrel separations and cracked and leaking aluminum cylinder heads. 2. Objectives of, and Legal Basis for, the Proposed Rule 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. 3. A Description of and an Estimate of the Number of Small Entities to Which the Proposed Rule Will Apply The FAA identified 432 small part 135 operators on which the rule will have a significant economic impact. We estimate that these small part 135 operators have assets valued between $22 thousand and $21 million. 4. Reporting, Record Keeping, and Other Compliance Requirements of the Proposed Rule 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. Total paperwork costs range between $7 and $623 per small entity. tkelley on DSK3SPTVN1PROD with PROPOSALS 5. Duplicative, Overlapping, or Conflicting Federal Rules The FAA is unaware of any Federal rules that duplicate, overlap, or conflict with this rule. (2) Periodic inspections only (no forced removals)—Though the National Transportation Safety Board recommends this option, we do not find it acceptable. The rate of crack growth to failure is unknown, but has shown that it can be more rapid than the intervals of part 43 mandated inspections. Further, failure events tend to group in both low time (<500 hr) failure events and high time (≤1000 hr) failure events. (3) Forced removals only (no periodic inspections)—We do not find that this option is acceptable. Failure events may still occur at times other than the low and high times groups described above, and periodic inspections may find impending failures. Comments Invited We invite you to send any written relevant data, views, or arguments about this rulemaking. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2012–0002; Directorate Identifier 2011– NE–42–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this rulemaking action. The most helpful comments will reference a specific portion of the IRFA or related rulemaking document, explain the reason for any recommended change, and include supporting data. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will address all comments in the final rule including those already in the AD docket from the NPRM. We will also post a report summarizing each substantive verbal contact we receive about the proposed AD. Issued in Burlington, Massachusetts, on February 27, 2014. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2014–05234 Filed 3–11–14; 8:45 am] BILLING CODE 4910–13–P 6. Significant Alternatives to the Proposed Rule We have considered the following alternatives: (1) Do nothing—This option is not acceptable due to the number of failures of ECi cylinder head assemblies and the consequences of the failures. VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 13925 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0139; Directorate Identifier 2012–NM–133–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2009–20– 05 that applies to certain Model A318, A319, A320, and A321 series airplanes. AD 2009–20–05 requires one-time inspections for cracking, damage, correct installation, and correct adjustment of the main landing gear (MLG) door hinge and actuator fittings on the keel beam, and corrective actions if necessary. Since we issued AD 2009– 20–05, we have received reports of cracks on fittings that had successfully passed the required inspections. This proposed AD would expand the applicability, reduce the compliance time, and require repetitive inspections instead of the one-time inspection. This proposed AD would also require revising the maintenance or inspection program to remove a certain airworthiness limitations item (ALI) task. We are proposing this AD to detect and correct such cracking, which could lead to in-flight detachment of an MLG door, possibly resulting in injury to persons on the ground and/or damage to the airplane. DATES: We must receive comments on this proposed AD by April 28, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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, Airworthiness Office—EIAS, 1 Rond SUMMARY: E:\FR\FM\12MRP1.SGM 12MRP1 13926 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this 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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0139; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1405; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: tkelley on DSK3SPTVN1PROD with PROPOSALS 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–2014–0139; Directorate Identifier 2012–NM–133–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// 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 September 15, 2009, we issued AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009). AD 2009–20–05 requires actions intended to address an unsafe condition on certain Model A318, A319, A320, and A321 series airplanes. VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 Since we issued AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009), we have received reports of cracks on fittings that had successfully passed the required inspections. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012– 0118, dated July 4, 2012 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Several cases of cracks have reportedly been found on the MLG door hinge fitting and on the MLG door actuator fitting on the keel beam. This condition, if not detected and corrected, could lead to in-flight detachment of a MLG door, possibly resulting in injury to persons on the ground and/or damage to the aeroplane. To address this potential unsafe condition, EASA issued EASA AD 2007–0161 [http:// ad.easa.europa.eu/blob/easa_ad_2007_0161_ superseded.pdf/AD_2007-0161_1] [which corresponds to FAA AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009)], to require a one-time inspection of the affected fittings and accomplishment of the applicable corrective actions. Since that [EASA] AD was issued, some cracks have been found on fittings that had successfully passed the one-time inspection as required by EASA AD 2007–0161. Analyses of these cracks have lead Airbus to reconsider the repetitive inspections of the MLG door hinge and actuator fittings on the keel beam, in accordance with the ALI task 533154–02–1 requirement as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items (ALI) Document, by introducing more restrictive inspection thresholds and intervals. For the reasons stated above, this [EASA] AD, which supersedes EASA AD 2007–0161 and the ALI [Airworthiness Limitations Item] task 533154–02–1 requirements, expands the [EASA] AD applicability to all A318/A319/ A320/A321 aeroplanes and requires repetitive inspections of the MLG door hinge and actuator fittings on the keel beam at a new threshold and interval and, depending on findings, the accomplishment of applicable corrective actions. The inspections are detailed, high frequency eddy current (HFEC), and ultrasonic inspections for cracking, damage, correct installation, and correct adjustment, as applicable. The corrective actions include correcting incorrect adjustments and installations, and repair. Additionally, this proposed AD would require, for certain airplanes, contacting the FAA for instructions on repairs and accomplishing those instructions. This proposed AD would also require revising the maintenance PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 program to remove ALI task 533154–02– 1. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA– 2014–0139. Relevant Service Information Airbus has issued Airbus Mandatory Service Bulletin A320–53–1195, Revision 03, including Service Bulletin Reporting Sheet, dated November 8, 2011; and Airbus Mandatory Service Bulletin A320–53–1196, Revision 02, including Service Bulletin Reporting Sheet, dated November 8, 2011. 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. Repair Approvals In many FAA transport ADs, when the service information specifies to contact the manufacturer for further instructions if certain discrepancies are found, we typically include in the AD a requirement to accomplish the action using a method approved by either the FAA or the State of Design Authority (or its delegated agent). We have recently been notified that certain laws in other countries do not allow such delegation of authority, but some countries do recognize design approval organizations. In addition, we have become aware that some U.S. operators have used repair instructions that were previously approved by a State of Design Authority or a Design Approval Holder (DAH) as a method of compliance with this provision in FAA ADs. Frequently, in these cases, the previously approved repair instructions come from the airplane structural repair manual or the DAH repair approval statements that were not specifically developed to address the unsafe condition corrected by the AD. Using repair instructions that were not specifically approved for a particular AD creates the potential for doing E:\FR\FM\12MRP1.SGM 12MRP1 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules repairs that were not developed to address the unsafe condition identified by the MCAI AD, the FAA AD, or the applicable service information, which could result in the unsafe condition not being fully corrected. To prevent the use of repairs that were not specifically developed to correct the unsafe condition, certain requirements specified in this proposed AD require that the repair approval specifically refer to the FAA AD. This change is intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we use the phrase ‘‘its delegated agent, or the DAH with State of Design Authority design organization approval, as applicable’’ in this proposed AD to refer to a DAH authorized to approve certain required repairs for this proposed AD. tkelley on DSK3SPTVN1PROD with PROPOSALS Differences Between This AD and the MCAI or Service Information The MCAI specifies for airplanes on which a Repair Approval Sheet (RAS) has been issued by Airbus to cover findings from an inspection performed before the effective date of this AD, as described in certain Airbus documents, accomplishing the RAS instructions and thereafter doing the repetitive inspections specified in the MCAI. This proposed AD does not require those actions as mandated by the MCAI. However, we would like to clarify that an RAS issued by the DAH under the authority of EASA’s DOA is an approved method of repair. This difference has been coordinated with the EASA. Costs of Compliance We estimate that this proposed AD affects 851 airplanes of U.S. registry. The actions that are required by AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009), and retained in this proposed AD take about 28 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2009–20–05 is $2,380 per product. We also estimate that it would take about 26 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $1,880,710, or $2,210 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. VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to 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 control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is 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. 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; PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 13927 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009), and adding the following new AD: ■ Airbus: Docket No. FAA–2014–0139; Directorate Identifier 2012–NM–133–AD. (a) Comments Due Date We must receive comments by April 28, 2014. (b) Affected ADs This AD supersedes AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009). (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks on the main landing gear (MLG) door hinge fitting and actuator fitting on the keel beam. We are issuing this AD to detect and correct such cracking, which could lead to in-flight detachment of an MLG door, possibly resulting in injury to persons on the ground and/or damage to the airplane. E:\FR\FM\12MRP1.SGM 12MRP1 13928 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules tkelley on DSK3SPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained One-Time Inspections and Corrective Action This paragraph restates the requirements of paragraphs (f)(1) and (f)(2) of AD 2009–20– 05, Amendment 39–16028 (74 FR 49795, September 29, 2009). For airplanes having serial numbers up to manufacturer’s serial number (MSN) 2850 inclusive, except MSNs 0115, 0184, 0782, 1151, 1190, 2650, 2675, 2706, 2801, and 2837: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD. (1) At the latest of the times specified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD: Perform detailed visual, high frequency eddy current (HFEC), and ultrasonic inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the left-hand (LH) and righthand (RH) MLG door actuator fitting on the keel beam, and do all applicable corrective actions before further flight, except as provided by paragraph (h) of this AD. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–53–1195, Revision 02, including Appendix 01, dated April 5, 2007; except where that service information specifies that the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. As of the effective date of this AD, repair using a method approved by the Manager, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder (DAH) with the EASA design organization approval, as applicable). For a repair method to be approved as of the effective date of this AD, the repair approval must specifically refer to this AD. (i) Within 6,000 flight cycles since first flight. (ii) Within 1,500 flight cycles after November 3, 2009 (the effective date of AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009)). (iii) Within 6,000 flight cycles from the latest MLG door actuator fitting replacement. (2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: Perform detailed visual and HFEC inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door hinge fitting on the keel beam, and do all applicable corrective actions before further flight, except as provided by paragraph (h) of this AD. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–53–1196, Revision 01, including Appendix 01, dated November 29, 2006; except where that service information specifies that the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. As of the effective date of this AD, repair using a VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 method approved by the Manager, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder (DAH) with the EASA design organization approval, as applicable). For a repair method to be approved as of the effective date of this AD, the repair approval must specifically refer to this AD. (i) Within 4,500 flight cycles since first flight. (ii) Within 1,500 flight cycles after November 3, 2009 (the effective date of AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009)). (h) Retained Exception to Paragraph (g) of This AD This paragraph restates the exception specified in paragraph (f)(4) of AD 2009–20– 05, Amendment 39–16028 (74 FR 49795, September 29, 2009). Where the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–53–1195, Revision 02, including Appendix 01, dated April 5, 2007; or Airbus Mandatory Service Bulletin A320–53–1196, Revision 01, including Appendix 01, dated November 29, 2006; specify to submit a report where no damage or crack is found during the inspection required by paragraph (g)(1) or (g)(2) of this AD: Send the report to Airbus using the applicable reporting sheet in Appendix 01 of Airbus Mandatory Service Bulletin A320–53–1195, Revision 02, dated April 5, 2007; or Airbus Mandatory Service Bulletin A320–53–1196, Revision 01, dated November 29, 2006. Send the report at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) If the inspection was done on or after November 3, 2009 (the effective date of AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009)): Submit the report within 30 days after the inspection. (2) If the inspection was done before November 3, 2009 (the effective date of AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009)): Submit the report within 30 days after November 3, 2009. (i) New Repetitive Inspections and Corrective Action (1) At the latest of the times specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD: Perform detailed, HFEC, and ultrasonic inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door actuator fitting on the keel beam, and do all applicable corrective actions before further flight. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–53–1195, Revision 03, including Service Bulletin Reporting Sheet, dated November 8, 2011; except where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent, or the Design Approval Holder (DAH) with the EASA PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 design organization approval, as applicable). For a repair method to be approved, the repair approval must specifically refer to this AD. Repeat the inspections thereafter at intervals not to exceed 2,250 flight cycles. (i) Before the accumulation of 3,000 flight cycles since first flight. (ii) Within 2,250 flight cycles after the most recent inspection done as specified in Airbus Service Bulletin A320–53–1195, or Task 533154–02–1 of the Airbus A318/A319/ A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitations Items (DT ALI), as applicable. (iii) Within 1,500 flight cycles after the effective date of this AD. (2) At the latest of the times specified in paragraphs (i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of this AD: Perform detailed and HFEC inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door hinge fitting on the keel beam, and do all applicable corrective actions before further flight. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320–53–1196, Revision 02, including Service Bulletin Reporting Sheet, dated November 8, 2011; except where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent, or the DAH with the EASA design organization approval, as applicable). For a repair method to be approved, the repair approval must specifically refer to this AD. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles. (i) Before the accumulation of 3,000 flight cycles since first flight. (ii) Within 3,000 flight cycles after the most recent inspection done as specified in Airbus Service Bulletin A320–53–1196, or Task 533154–02–1 of the Airbus A318/A319/ A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitations Items (DT ALI), as applicable. (iii) Within 1,500 flight cycles after the effective date of this AD. (j) New Corrective Action Limitation The accomplishment of a corrective action on an airplane, as required by paragraph (i) of this AD, does not constitute terminating action for the repetitive inspection requirements of this AD for that airplane. (k) New Maintenance or Inspection Program Revision After the effective date of this AD and before further flight after doing the inspection required by paragraph (i) of this AD: Revise the maintenance or inspection program, as applicable, to remove Task 533154–02–1 of the Airbus A318/A319/ A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 2012. The actions required by this AD take precedence over Task 533154–02–1 of the Airbus A318/A319/ A320/A321 ALS Part 2—Damage Tolerant E:\FR\FM\12MRP1.SGM 12MRP1 Federal Register / Vol. 79, No. 48 / Wednesday, March 12, 2014 / Proposed Rules Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 2012. tkelley on DSK3SPTVN1PROD with PROPOSALS (l) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227 1405; fax (425) 227– 1149. Information may be emailed to: 9ANM-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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the DAH with a State of Design Authority’s design organization approval, as applicable). You are required to ensure 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information European Aviation Safety Agency Airworthiness Directive 2012–0118, dated July 4, 2012, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0139. (2) For service information identified in this AD, contact Airbus, Airworthiness VerDate Mar<15>2010 17:07 Mar 11, 2014 Jkt 232001 Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. You may view this 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 February 28, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–05434 Filed 3–11–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0140; Directorate Identifier 2013–NM–176–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes. This proposed AD was prompted by a report of contact between certain electrical harnesses and the hatrack rod that could cause chafing between the harnesses and surrounding structure. This proposed AD would require modifying the routing of certain electrical harnesses. We are proposing this AD to prevent chafing and possible short circuit of two oxygen chemical generator containers in different wiring routes, which could result in malfunction of the electrical opening of all the containers connected to these routes. Such conditions, during a sudden depressurization event, could result in lack of oxygen and consequent injuries to airplane occupants. DATES: We must receive comments on this proposed AD by April 28, 2014 ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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 SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 13929 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 http://www.airbus.com. You may view this 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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0140; 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, WA 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–2014–0140; Directorate Identifier 2013–NM–176–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any E:\FR\FM\12MRP1.SGM 12MRP1

Agencies

[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Proposed Rules]
[Pages 13925-13929]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-05434]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0139; Directorate Identifier 2012-NM-133-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 airworthiness directive (AD) 2009-20-
05 that applies to certain Model A318, A319, A320, and A321 series 
airplanes. AD 2009-20-05 requires one-time inspections for cracking, 
damage, correct installation, and correct adjustment of the main 
landing gear (MLG) door hinge and actuator fittings on the keel beam, 
and corrective actions if necessary. Since we issued AD 2009-20-05, we 
have received reports of cracks on fittings that had successfully 
passed the required inspections. This proposed AD would expand the 
applicability, reduce the compliance time, and require repetitive 
inspections instead of the one-time inspection. This proposed AD would 
also require revising the maintenance or inspection program to remove a 
certain airworthiness limitations item (ALI) task. We are proposing 
this AD to detect and correct such cracking, which could lead to in-
flight detachment of an MLG door, possibly resulting in injury to 
persons on the ground and/or damage to the airplane.

DATES: We must receive comments on this proposed AD by April 28, 2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://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, Airworthiness Office--EIAS, 1 Rond

[[Page 13926]]

Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 
93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. You may view this 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0139; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405; 
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-2014-0139; 
Directorate Identifier 2012-NM-133-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://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 September 15, 2009, we issued AD 2009-20-05, Amendment 39-16028 
(74 FR 49795, September 29, 2009). AD 2009-20-05 requires actions 
intended to address an unsafe condition on certain Model A318, A319, 
A320, and A321 series airplanes.
    Since we issued AD 2009-20-05, Amendment 39-16028 (74 FR 49795, 
September 29, 2009), we have received reports of cracks on fittings 
that had successfully passed the required inspections. The European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Community, has issued EASA Airworthiness 
Directive 2012-0118, dated July 4, 2012 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    Several cases of cracks have reportedly been found on the MLG 
door hinge fitting and on the MLG door actuator fitting on the keel 
beam.
    This condition, if not detected and corrected, could lead to in-
flight detachment of a MLG door, possibly resulting in injury to 
persons on the ground and/or damage to the aeroplane.
    To address this potential unsafe condition, EASA issued EASA AD 
2007-0161 [http://ad.easa.europa.eu/blob/easa_ad_2007_0161_superseded.pdf/AD_2007-0161_1] [which corresponds to FAA AD 2009-
20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)], to 
require a one-time inspection of the affected fittings and 
accomplishment of the applicable corrective actions.
    Since that [EASA] AD was issued, some cracks have been found on 
fittings that had successfully passed the one-time inspection as 
required by EASA AD 2007-0161. Analyses of these cracks have lead 
Airbus to reconsider the repetitive inspections of the MLG door 
hinge and actuator fittings on the keel beam, in accordance with the 
ALI task 533154-02-1 requirement as defined in Airbus A318/A319/
A320/A321 Airworthiness Limitation Items (ALI) Document, by 
introducing more restrictive inspection thresholds and intervals.
    For the reasons stated above, this [EASA] AD, which supersedes 
EASA AD 2007-0161 and the ALI [Airworthiness Limitations Item] task 
533154-02-1 requirements, expands the [EASA] AD applicability to all 
A318/A319/A320/A321 aeroplanes and requires repetitive inspections 
of the MLG door hinge and actuator fittings on the keel beam at a 
new threshold and interval and, depending on findings, the 
accomplishment of applicable corrective actions.

    The inspections are detailed, high frequency eddy current (HFEC), 
and ultrasonic inspections for cracking, damage, correct installation, 
and correct adjustment, as applicable. The corrective actions include 
correcting incorrect adjustments and installations, and repair. 
Additionally, this proposed AD would require, for certain airplanes, 
contacting the FAA for instructions on repairs and accomplishing those 
instructions. This proposed AD would also require revising the 
maintenance program to remove ALI task 533154-02-1. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2014-0139.

Relevant Service Information

    Airbus has issued Airbus Mandatory Service Bulletin A320-53-1195, 
Revision 03, including Service Bulletin Reporting Sheet, dated November 
8, 2011; and Airbus Mandatory Service Bulletin A320-53-1196, Revision 
02, including Service Bulletin Reporting Sheet, dated November 8, 2011. 
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.

Repair Approvals

    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing

[[Page 13927]]

repairs that were not developed to address the unsafe condition 
identified by the MCAI AD, the FAA AD, or the applicable service 
information, which could result in the unsafe condition not being fully 
corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, certain requirements specified in this 
proposed AD require that the repair approval specifically refer to the 
FAA AD. This change is intended to clarify the method of compliance and 
to provide operators with better visibility of repairs that are 
specifically developed and approved to correct the unsafe condition. In 
addition, we use the phrase ``its delegated agent, or the DAH with 
State of Design Authority design organization approval, as applicable'' 
in this proposed AD to refer to a DAH authorized to approve certain 
required repairs for this proposed AD.

Differences Between This AD and the MCAI or Service Information

    The MCAI specifies for airplanes on which a Repair Approval Sheet 
(RAS) has been issued by Airbus to cover findings from an inspection 
performed before the effective date of this AD, as described in certain 
Airbus documents, accomplishing the RAS instructions and thereafter 
doing the repetitive inspections specified in the MCAI. This proposed 
AD does not require those actions as mandated by the MCAI. However, we 
would like to clarify that an RAS issued by the DAH under the authority 
of EASA's DOA is an approved method of repair. This difference has been 
coordinated with the EASA.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    The actions that are required by AD 2009-20-05, Amendment 39-16028 
(74 FR 49795, September 29, 2009), and retained in this proposed AD 
take about 28 work-hours per product, at an average labor rate of $85 
per work-hour. Based on these figures, the estimated cost of the 
actions that were required by AD 2009-20-05 is $2,380 per product.
    We also estimate that it would take about 26 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $1,880,710, or 
$2,210 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.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is 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.

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.

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

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 airworthiness directive (AD) 
2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009), and 
adding the following new AD:

Airbus: Docket No. FAA-2014-0139; Directorate Identifier 2012-NM-
133-AD.

(a) Comments Due Date

    We must receive comments by April 28, 2014.

(b) Affected ADs

    This AD supersedes AD 2009-20-05, Amendment 39-16028 (74 FR 
49795, September 29, 2009).

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any 
category, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracks on the main landing 
gear (MLG) door hinge fitting and actuator fitting on the keel beam. 
We are issuing this AD to detect and correct such cracking, which 
could lead to in-flight detachment of an MLG door, possibly 
resulting in injury to persons on the ground and/or damage to the 
airplane.

[[Page 13928]]

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained One-Time Inspections and Corrective Action

    This paragraph restates the requirements of paragraphs (f)(1) 
and (f)(2) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, 
September 29, 2009). For airplanes having serial numbers up to 
manufacturer's serial number (MSN) 2850 inclusive, except MSNs 0115, 
0184, 0782, 1151, 1190, 2650, 2675, 2706, 2801, and 2837: Do the 
actions required by paragraphs (g)(1) and (g)(2) of this AD.
    (1) At the latest of the times specified in paragraphs 
(g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD: Perform detailed 
visual, high frequency eddy current (HFEC), and ultrasonic 
inspections (for cracking, damage, correct installation, and correct 
adjustment, as applicable) of the left-hand (LH) and right-hand (RH) 
MLG door actuator fitting on the keel beam, and do all applicable 
corrective actions before further flight, except as provided by 
paragraph (h) of this AD. Do all actions required by this paragraph 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A320-53-1195, Revision 02, including 
Appendix 01, dated April 5, 2007; except where that service 
information specifies that the applicable corrective action is 
contacting Airbus, contact Airbus for repair instructions and repair 
before further flight. As of the effective date of this AD, repair 
using a method approved by the Manager, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or 
its delegated agent, or the Design Approval Holder (DAH) with the 
EASA design organization approval, as applicable). For a repair 
method to be approved as of the effective date of this AD, the 
repair approval must specifically refer to this AD.
    (i) Within 6,000 flight cycles since first flight.
    (ii) Within 1,500 flight cycles after November 3, 2009 (the 
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, 
September 29, 2009)).
    (iii) Within 6,000 flight cycles from the latest MLG door 
actuator fitting replacement.
    (2) At the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD: Perform detailed visual and HFEC 
inspections (for cracking, damage, correct installation, and correct 
adjustment, as applicable) of the LH and RH MLG door hinge fitting 
on the keel beam, and do all applicable corrective actions before 
further flight, except as provided by paragraph (h) of this AD. Do 
all actions required by this paragraph in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-53-1196, Revision 01, including Appendix 01, dated November 29, 
2006; except where that service information specifies that the 
applicable corrective action is contacting Airbus, contact Airbus 
for repair instructions and repair before further flight. As of the 
effective date of this AD, repair using a method approved by the 
Manager, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA) (or its delegated agent, or 
the Design Approval Holder (DAH) with the EASA design organization 
approval, as applicable). For a repair method to be approved as of 
the effective date of this AD, the repair approval must specifically 
refer to this AD.
    (i) Within 4,500 flight cycles since first flight.
    (ii) Within 1,500 flight cycles after November 3, 2009 (the 
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, 
September 29, 2009)).

(h) Retained Exception to Paragraph (g) of This AD

    This paragraph restates the exception specified in paragraph 
(f)(4) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 
29, 2009). Where the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A320-53-1195, Revision 02, including Appendix 01, 
dated April 5, 2007; or Airbus Mandatory Service Bulletin A320-53-
1196, Revision 01, including Appendix 01, dated November 29, 2006; 
specify to submit a report where no damage or crack is found during 
the inspection required by paragraph (g)(1) or (g)(2) of this AD: 
Send the report to Airbus using the applicable reporting sheet in 
Appendix 01 of Airbus Mandatory Service Bulletin A320-53-1195, 
Revision 02, dated April 5, 2007; or Airbus Mandatory Service 
Bulletin A320-53-1196, Revision 01, dated November 29, 2006. Send 
the report at the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD.
    (1) If the inspection was done on or after November 3, 2009 (the 
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, 
September 29, 2009)): Submit the report within 30 days after the 
inspection.
    (2) If the inspection was done before November 3, 2009 (the 
effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, 
September 29, 2009)): Submit the report within 30 days after 
November 3, 2009.

(i) New Repetitive Inspections and Corrective Action

    (1) At the latest of the times specified in paragraphs 
(i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD: Perform detailed, 
HFEC, and ultrasonic inspections (for cracking, damage, correct 
installation, and correct adjustment, as applicable) of the LH and 
RH MLG door actuator fitting on the keel beam, and do all applicable 
corrective actions before further flight. Do all actions required by 
this paragraph in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A320-53-1195, Revision 03, 
including Service Bulletin Reporting Sheet, dated November 8, 2011; 
except where that service information specifies that the applicable 
corrective action is contacting Airbus, before further flight, 
repair using a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the EASA (or its 
delegated agent, or the Design Approval Holder (DAH) with the EASA 
design organization approval, as applicable). For a repair method to 
be approved, the repair approval must specifically refer to this AD. 
Repeat the inspections thereafter at intervals not to exceed 2,250 
flight cycles.
    (i) Before the accumulation of 3,000 flight cycles since first 
flight.
    (ii) Within 2,250 flight cycles after the most recent inspection 
done as specified in Airbus Service Bulletin A320-53-1195, or Task 
533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2--Damage 
Tolerant Airworthiness Limitations Items (DT ALI), as applicable.
    (iii) Within 1,500 flight cycles after the effective date of 
this AD.
    (2) At the latest of the times specified in paragraphs 
(i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of this AD: Perform detailed 
and HFEC inspections (for cracking, damage, correct installation, 
and correct adjustment, as applicable) of the LH and RH MLG door 
hinge fitting on the keel beam, and do all applicable corrective 
actions before further flight. Do all actions required by this 
paragraph in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A320-53-1196, Revision 02, 
including Service Bulletin Reporting Sheet, dated November 8, 2011; 
except where that service information specifies that the applicable 
corrective action is contacting Airbus, before further flight, 
repair using a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the EASA (or its 
delegated agent, or the DAH with the EASA design organization 
approval, as applicable). For a repair method to be approved, the 
repair approval must specifically refer to this AD. Repeat the 
inspections thereafter at intervals not to exceed 3,000 flight 
cycles.
    (i) Before the accumulation of 3,000 flight cycles since first 
flight.
    (ii) Within 3,000 flight cycles after the most recent inspection 
done as specified in Airbus Service Bulletin A320-53-1196, or Task 
533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2--Damage 
Tolerant Airworthiness Limitations Items (DT ALI), as applicable.
    (iii) Within 1,500 flight cycles after the effective date of 
this AD.

(j) New Corrective Action Limitation

    The accomplishment of a corrective action on an airplane, as 
required by paragraph (i) of this AD, does not constitute 
terminating action for the repetitive inspection requirements of 
this AD for that airplane.

(k) New Maintenance or Inspection Program Revision

    After the effective date of this AD and before further flight 
after doing the inspection required by paragraph (i) of this AD: 
Revise the maintenance or inspection program, as applicable, to 
remove Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 
2--Damage Tolerant Airworthiness Limitations Items (DT ALI), 
Revision 01, dated April 4, 2012. The actions required by this AD 
take precedence over Task 533154-02-1 of the Airbus A318/A319/A320/
A321 ALS Part 2--Damage Tolerant

[[Page 13929]]

Airworthiness Limitations Items (DT ALI), Revision 01, dated April 
4, 2012.

(l) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227 1405; 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.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the DAH with a State of Design Authority's 
design organization approval, as applicable). You are required to 
ensure 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
European Aviation Safety Agency Airworthiness Directive 2012-0118, 
dated July 4, 2012, for related information. This MCAI may be found 
in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2014-0139.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this 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 February 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-05434 Filed 3-11-14; 8:45 am]
BILLING CODE 4910-13-P