Airworthiness Directives; Airbus Airplanes, 11096-11101 [2015-02692]

Download as PDF wreier-aviles on DSK5TPTVN1PROD with RULES 11096 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations (3) Continuing education/training standards for State directors of school nutrition programs and distributing agencies. Each school year, all State directors with responsibility for the National School Lunch Program under part 210 of this chapter and the School Breakfast Program under part 220 of this chapter, as well as those responsible for the distribution of USDA donated foods under part 250 of this chapter, must complete a minimum of 15 hours of training in core areas that may include nutrition, operations, administration, communications and marketing. Additional hours and topics may be specified by FNS, as needed, to address Program integrity and other critical issues. (4) Provision of annual training. At least annually, State agencies with responsibility for the National School Lunch Program under part 210 of this chapter and the School Breakfast Program under part 220 of this chapter, as well as State agencies with responsibility for the distribution of USDA donated foods under part 250 of this chapter, must provide or ensure that State agency staff receive annual continuing education/training. (i) Each State agency with responsibility for the National School Lunch Program under part 210 of this chapter and the School Breakfast Program under part 220 of this chapter must provide a minimum of 18 hours of continuing education/training to school food authorities. Topics include administrative practices (including training in application, certification, verification, meal counting, and meal claiming procedures); the accuracy of approvals for free and reduced price meals; the identification of reimbursable meals at the point of service; nutrition; health and food safety standards; the efficient and effective use of USDA donated foods; and any other appropriate topics, as determined by FNS, to ensure program compliance and integrity or to address other critical issues. (ii) Each State agency with responsibility for the distribution of USDA donated foods under part 250 of this chapter must provide or ensure receipt of continuing education/training to State distribution agency staff on an annual basis. Topics may include the efficient and effective use of USDA donated foods; inventory rotation and control; health and food safety standards; and any other appropriate topics, as determined by FNS, to ensure program compliance and integrity or to address other critical issues. (5) Records and recordkeeping. State agencies must annually retain records for a period of three years to adequately VerDate Sep<11>2014 17:37 Feb 27, 2015 Jkt 235001 demonstrate compliance with the professional standards for State directors of school nutrition programs established in this paragraph. (6) Failure to comply. Failure to comply with the professional standards in this paragraph may result in sanctions as specified in paragraph (b) of this section. ■ 13. Revise § 235.12 to read as follows: § 235.12 Information collection/ recordkeeping—OMB assigned control numbers. 7 CFR Section where requirements are described Current OMB control No. 235.3(b) .......... 235.4 ............... 235.5(b), (d) .... 235.7(a), (b) .... 235.9(c), (d) .... 235.11 ............. 210.7 ............... 0584–0067. 0584–0067. 0584–0067. 0584–0067. 0584–0067. 0584–0067. 0584–0067. Dated: February 24, 2015. Audrey Rowe, Administrator, Food and Nutrition Service. [FR Doc. 2015–04234 Filed 2–27–15; 8:45 am] BILLING CODE 3410–30–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0139; Directorate Identifier 2012–NM–133–AD; Amendment 39–18081; AD 2015–02–14] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2009–20– 05 for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2009–20–05 required 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. This new AD expands the applicability, reduces the compliance time, and requires repetitive inspections instead of the one-time inspection. This AD also requires revising the maintenance or inspection program. This AD was prompted by reports of SUMMARY: PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 cracks on fittings that had successfully passed certain required inspections. We are issuing this AD to detect and correct cracking on the MLG door hinge fitting and actuator fitting on the keel beam, 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: This AD becomes effective April 6, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 6, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 3, 2009 (74 FR 49795, September 29, 2009). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0139; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. 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.airwortheas@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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0139. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009–20–05, Amendment 39–16028 (74 FR 49795, September 29, 2009). AD 2009–20–05 applied to certain Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on March 12, 2014 (79 FR 13925). E:\FR\FM\02MRR1.SGM 02MRR1 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, 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 on the specified products. The MCAI states: wreier-aviles on DSK5TPTVN1PROD with RULES 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. This AD also requires revising the maintenance or inspection program, as applicable, to remove ALI task 533154–02–1. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-01390002. Comments We gave the public the opportunity to participate in developing this AD. The VerDate Sep<11>2014 14:17 Feb 27, 2015 Jkt 235001 following presents the comments received on the NPRM (79 FR 13925, March 12, 2014) and the FAA’s response to each comment. Requests To Reference Revised Service Bulletins Airbus and United Airlines (UAL) requested that we reference Airbus Service Bulletin A320–53–1195, Revision 05, dated November 22, 2013; and Airbus Service Bulletin A320–53– 1196, Revision 04, dated November 22, 2013; as appropriate sources of service information. We agree with the commenters’ requests to reference Airbus Service Bulletin A320–53–1195, Revision 05, dated November 22, 2013; and Airbus Service Bulletin A320–53–1196, Revision 04, dated November 22, 2013; as appropriate sources of service information for accomplishing the required actions in this AD. No additional work is specified by these service bulletin revisions for airplanes modified by any previous issue. We added a new paragraph (l) to this AD and redesignated subsequent paragraphs accordingly. New paragraph (l) gives credit for actions accomplished using certain service information before the effective date of this AD. We have revised paragraph (i)(1) of this AD to refer to Airbus Service Bulletin A320–53–1195, Revision 05, dated November 22, 2013, and added paragraph (l)(1) to this AD to give credit for actions accomplished previously using Airbus Service Bulletin A320–53– 1195, Revision 03, dated November 8, 2011; or Airbus Service Bulletin A320– 53–1195, Revision 04, dated August 22, 2012. We have revised paragraph (i)(2) of this AD to refer to Airbus Service Bulletin A320–53–1196, Revision 04, dated November 22, 2013; and added paragraph (l)(2) to this AD to give credit for actions accomplished using Airbus Service Bulletin A320–53–1196, Revision 02, dated November 8, 2011; or Airbus Service Bulletin A320–53–1196, Revision 03, dated August 22, 2012. Request To Refer to Additional Service Information for Task Removal UAL requested that we revise paragraph (k) of the proposed AD (79 FR 13925, March 12, 2014) to reference Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/S–M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010; in addition to Airbus A318/A319/A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 2012. UAL stated that PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 11097 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, is ‘‘superseded by Airbus Service Bulletins A320–53–1195 and A320–53–1196.’’ UAL explained that operators that comply with Airbus A318/A319/A320/A321 ALS Part 2— Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 2012, should already have removed Task 533154–02–1 from their maintenance/inspection programs. UAL also explained that operators might not have Airbus A318/A319/A320/A321 ALS Part 2—Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 2012, in their maintenance/inspection programs and instead might have Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010. We agree with the commenter’s request to refer to Airbus A318/A319/ A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/ 96, Issue 10, dated October 2009; or Issue 11, dated September 2010; in paragraph (k) of this AD. This revision will ensure that the actions specified by Task 533154–02–1 are removed from an operator’s maintenance inspection program. Request To Remove Reporting Requirement UAL requested that we not require reporting, as described in the service information, if no damage and/or cracks are found during the inspection of the hinge fittings. UAL stated that reporting has insignificant value and is a burden on the operator. UAL explained that, since the inspections must be repetitively accomplished, the rate of reporting no findings will be significant without adding valued information, and that any damage/cracks will be reported to Airbus when they are contacted for repair approval. We disagree with the commenter’s request to remove the reporting action required by this AD. A reporting requirement is instrumental in ensuring that we can gather as much information as possible regarding the extent and nature of the identified unsafe condition, especially in cases where that data may not be available through other established means. Also, the commenter did not provided any rationale concerning how eliminating the reporting requirement will ensure that future service information from Airbus will continue to maintain operational E:\FR\FM\02MRR1.SGM 02MRR1 11098 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations safety of the fleet. We have not changed this AD in this regard. wreier-aviles on DSK5TPTVN1PROD with RULES Request To Remove Requirement To Refer to This AD in Repair Approvals UAL requested that we remove the statement ‘‘for a repair method to be approved, the repair approval must specifically refer to this AD’’ in paragraph (i) of the proposed AD (79 FR 13925, March 12, 2014). UAL stated that this statement could have a significant impact on the financial cost and customer support between the operator and Airbus. UAL also stated that this statement should be removed for those general reasons stated in A4A’s comment on the same topic in NPRM 2012–NM–101–AD (78 FR 78285, December 26, 2013), which stated, among other justifications, that ‘‘The added costs for this AD and all that may follow bearing the new procedural wording represent an unfair burden placed solely on U.S. registered aircraft.’’ We concur with the commenter’s request to remove the requirement to include the AD reference in repair approvals. Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD. The MCAI or referenced service information in an FAA AD often directs the owner/ operator to contact the manufacturer for corrective actions, such as a repair. Briefly, the Airworthy Product paragraph allowed owners/operators to use corrective actions provided by the manufacturer if those actions were FAAapproved. In addition, the paragraph stated that any actions approved by the State of Design Authority (or its delegated agent) are considered to be FAA-approved. In the NPRM (79 FR 13925, March 12, 2014), we proposed to prevent the use of repairs that were not specifically developed to correct the unsafe condition, by requiring that the repair approval provided by the State of Design Authority or its delegated agent specifically refer to this FAA AD. This change was 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 proposed to change the phrase ‘‘its delegated agent’’ to include ‘‘the Design Approval Holder (DAH) with a State of Design Authority’s design organization approval (DOA)’’ to refer to a DAH authorized to approve required repairs for the AD. VerDate Sep<11>2014 14:17 Feb 27, 2015 Jkt 235001 Comments were provided to the NPRM (79 FR 13925, March 12, 2014) and to an NPRM referenced by the commenter (i.e., Directorate Identifier 2012–NM–101–AD (78 FR 78285, December 26, 2013)) about these proposed changes. One commenter to the NPRM having Directorate Identifier 2012–NM–101–AD, United Parcel Service (UPS), stated the following: ‘‘The proposed wording, being specific to repairs, eliminates the interpretation that Airbus messages are acceptable for approving minor deviations (corrective actions) needed during accomplishment of an AD mandated Airbus service bulletin.’’ This comment has made the FAA aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an AD-mandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed that paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, EASA, or Airbus’s EASA DOA. The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the document are EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility afforded previously by the PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the AD Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. Other commenters to NPRM 2012– NM–101–AD (78 FR 78285, December 26, 2013) pointed out that in many cases the foreign manufacturer’s service bulletin and the foreign authority’s MCAI may have been issued some time before the FAA AD. Therefore, the DOA may have provided U.S. operators with an approved repair, developed with full awareness of the unsafe condition, before the FAA AD is issued. Under these circumstances, to comply with the FAA AD, the operator would be required to go back to the manufacturer’s DOA and obtain a new approval document, adding time and expense to the compliance process with no safety benefit. Based on these comments, we removed the requirement from this AD that the DAH-provided repair specifically refer to this AD. Before adopting such a requirement in the future, the FAA will coordinate with affected DAHs and verify they are prepared to implement means to ensure that their repair approvals consider the unsafe condition addressed in an AD. Any such requirements will be adopted through the normal AD rulemaking process, including notice-and-comment procedures, when appropriate. We have also decided not to include a generic reference to either the ‘‘delegated agent’’ or the ‘‘DAH with State of Design Authority design organization approval,’’ but instead we will provide the specific delegation approval granted by the State of Design Authority for the DAH. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM (79 FR E:\FR\FM\02MRR1.SGM 02MRR1 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations 13925, March 12, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 13925, March 12, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A320–53–1195, Revision 05, dated November 22, 2013, which describes procedures for inspections of the MLG door actuator fittings on the keel beam, and corrective actions if necessary. We also reviewed Airbus Service Bulletin A320–53–1196, Revision 04, dated November 22, 2013, which describes procedures for inspections of the MLG door hinge fitting on the keel beam, and corrective actions if necessary. This service information is reasonably available; see ADDRESSES for ways to access this service information. wreier-aviles on DSK5TPTVN1PROD with RULES Costs of Compliance We estimate that this 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 AD take about 28 workhours 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 will take about 26 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this 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 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 VerDate Sep<11>2014 14:17 Feb 27, 2015 Jkt 235001 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0139; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 11099 Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 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: ■ 2015–02–14 Airbus: Amendment 39–18081. Docket No. FAA–2014–0139; Directorate Identifier 2012–NM–133–AD. (a) Effective Date This AD becomes effective April 6, 2015. (b) Affected ADs This AD replaces 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 (MSNs). (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 cracking on the MLG door hinge fitting and actuator fitting on the keel beam, 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\02MRR1.SGM 02MRR1 11100 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations wreier-aviles on DSK5TPTVN1PROD with RULES (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), with specific delegation approval language. For airplanes having serial numbers up to 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, where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (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, where that service information specifies that the applicable corrective action is contacting Airbus, before VerDate Sep<11>2014 14:17 Feb 27, 2015 Jkt 235001 further flight, repair using a method approved by the Manager, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. (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; as applicable; 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 Service Bulletin A320–53–1195, Revision 05, dated November 22, 2013; 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 Airbus’s EASA DOA. 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 described in Airbus Service Bulletin A320–53–1195, or PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Task 533154–02–1 of the Airbus A318/A319/ A320/A321 Airworthiness Limitations Section 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 Service Bulletin A320–53–1196, Revision 04, dated November 22, 2013; 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 Airbus’s EASA DOA. 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 described 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 Limitation 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; Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/ 95A.0252/96, Issue 10, dated October 2009; or Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96 Issue 11, dated September 2010. 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 Airworthiness Limitation Items (DT ALI), Revision 01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96, Issue 10, dated October 2009; and Airbus A318/A319/A320/ A321 Airworthiness Limitation Items, Document AI/SE–M4/95A.0252/96 Issue 11, dated September 2010. E:\FR\FM\02MRR1.SGM 02MRR1 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations wreier-aviles on DSK5TPTVN1PROD with RULES (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1195, Revision 03, dated November 8, 2011; or Airbus Service Bulletin A320–53–1195, Revision 04, dated August 22, 2012; which are not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (i)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1196, Revision 02, dated November 8, 2011; or Airbus Service Bulletin A320–53–1196, Revision 03, dated August 22, 2012; which are not incorporated by reference in 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: 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-116AMOC-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) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (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 VerDate Sep<11>2014 14:17 Feb 27, 2015 Jkt 235001 11101 be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. DEPARTMENT OF TRANSPORTATION (n) Related Information 14 CFR Part 39 (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2012–0118, dated July 4, 2012, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0139-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD. [Docket No. FAA–2014–0189; Directorate Identifier 2013–NM–181–AD; Amendment 39–18099; AD 2015–03–03] (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on April 6, 2015. (i) Airbus Service Bulletin A320–53–1195, Revision 05, dated November 22, 2013. (ii) Airbus Service Bulletin A320–53–1196, Revision 04, dated November 22, 2013. (4) The following service information was approved for IBR on November 3, 2009 (74 FR 49795, September 29, 2009). (i) Airbus Mandatory Service Bulletin A320–53–1195, Revision 02, including Appendix 01, dated April 5, 2007. (ii) Airbus Mandatory Service Bulletin A320–53–1196, Revision 01, including Appendix 01, dated November 29, 2006. (5) 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. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on February 4, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–02692 Filed 2–27–15; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes, Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). This AD was prompted by a report of chafing found on the overflow sensor harness of the surge tank, and subsequent contact between the electrical wiring and fuel tank structure. This AD requires a one-time inspection for chafing of the overflow sensor harness, and repair if necessary. This AD also requires modification of the sensor harness. We are issuing this AD to prevent chafing of the harness and subsequent contact between the electrical wiring and fuel tank structure, which could result in electrical arcing and a fuel tank explosion and consequent loss of the airplane. DATES: This AD becomes effective April 6, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 6, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0189 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus, Airworthiness Office—EAW, 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.airwortheas@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. SUMMARY: E:\FR\FM\02MRR1.SGM 02MRR1

Agencies

[Federal Register Volume 80, Number 40 (Monday, March 2, 2015)]
[Rules and Regulations]
[Pages 11096-11101]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02692]


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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; 
Amendment 39-18081; AD 2015-02-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2009-20-05 for 
certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 
2009-20-05 required 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. This new AD expands the applicability, reduces 
the compliance time, and requires repetitive inspections instead of the 
one-time inspection. This AD also requires revising the maintenance or 
inspection program. This AD was prompted by reports of cracks on 
fittings that had successfully passed certain required inspections. We 
are issuing this AD to detect and correct cracking on the MLG door 
hinge fitting and actuator fitting on the keel beam, 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: This AD becomes effective April 6, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 6, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
November 3, 2009 (74 FR 49795, September 29, 2009).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0139; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0139.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-20-05, Amendment 39-16028 (74 FR 49795, 
September 29, 2009). AD 2009-20-05 applied to certain Model A318, A319, 
A320, and A321 series airplanes. The NPRM published in the Federal 
Register on March 12, 2014 (79 FR 13925).

[[Page 11097]]

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, 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 on 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. This AD 
also requires revising the maintenance or inspection program, as 
applicable, to remove ALI task 533154-02-1. You may examine the MCAI in 
the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0139-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 13925, March 12, 2014) and the FAA's response to each comment.

Requests To Reference Revised Service Bulletins

    Airbus and United Airlines (UAL) requested that we reference Airbus 
Service Bulletin A320-53-1195, Revision 05, dated November 22, 2013; 
and Airbus Service Bulletin A320-53-1196, Revision 04, dated November 
22, 2013; as appropriate sources of service information.
    We agree with the commenters' requests to reference Airbus Service 
Bulletin A320-53-1195, Revision 05, dated November 22, 2013; and Airbus 
Service Bulletin A320-53-1196, Revision 04, dated November 22, 2013; as 
appropriate sources of service information for accomplishing the 
required actions in this AD. No additional work is specified by these 
service bulletin revisions for airplanes modified by any previous 
issue. We added a new paragraph (l) to this AD and redesignated 
subsequent paragraphs accordingly. New paragraph (l) gives credit for 
actions accomplished using certain service information before the 
effective date of this AD.
    We have revised paragraph (i)(1) of this AD to refer to Airbus 
Service Bulletin A320-53-1195, Revision 05, dated November 22, 2013, 
and added paragraph (l)(1) to this AD to give credit for actions 
accomplished previously using Airbus Service Bulletin A320-53-1195, 
Revision 03, dated November 8, 2011; or Airbus Service Bulletin A320-
53-1195, Revision 04, dated August 22, 2012.
    We have revised paragraph (i)(2) of this AD to refer to Airbus 
Service Bulletin A320-53-1196, Revision 04, dated November 22, 2013; 
and added paragraph (l)(2) to this AD to give credit for actions 
accomplished using Airbus Service Bulletin A320-53-1196, Revision 02, 
dated November 8, 2011; or Airbus Service Bulletin A320-53-1196, 
Revision 03, dated August 22, 2012.

Request To Refer to Additional Service Information for Task Removal

    UAL requested that we revise paragraph (k) of the proposed AD (79 
FR 13925, March 12, 2014) to reference Airbus A318/A319/A320/A321 
Airworthiness Limitation Items, Document AI/S-M4/95A.0252/96, Issue 10, 
dated October 2009; or Issue 11, dated September 2010; in addition to 
Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant Airworthiness 
Limitations Items (DT ALI), Revision 01, dated April 4, 2012. UAL 
stated that 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, is ``superseded by Airbus Service Bulletins 
A320-53-1195 and A320-53-1196.'' UAL explained that operators that 
comply with Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant 
Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 
2012, should already have removed Task 533154-02-1 from their 
maintenance/inspection programs. UAL also explained that operators 
might not have Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant 
Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 
2012, in their maintenance/inspection programs and instead might have 
Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/
SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated 
September 2010.
    We agree with the commenter's request to refer to Airbus A318/A319/
A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/
96, Issue 10, dated October 2009; or Issue 11, dated September 2010; in 
paragraph (k) of this AD. This revision will ensure that the actions 
specified by Task 533154-02-1 are removed from an operator's 
maintenance inspection program.

Request To Remove Reporting Requirement

    UAL requested that we not require reporting, as described in the 
service information, if no damage and/or cracks are found during the 
inspection of the hinge fittings. UAL stated that reporting has 
insignificant value and is a burden on the operator. UAL explained 
that, since the inspections must be repetitively accomplished, the rate 
of reporting no findings will be significant without adding valued 
information, and that any damage/cracks will be reported to Airbus when 
they are contacted for repair approval.
    We disagree with the commenter's request to remove the reporting 
action required by this AD. A reporting requirement is instrumental in 
ensuring that we can gather as much information as possible regarding 
the extent and nature of the identified unsafe condition, especially in 
cases where that data may not be available through other established 
means. Also, the commenter did not provided any rationale concerning 
how eliminating the reporting requirement will ensure that future 
service information from Airbus will continue to maintain operational

[[Page 11098]]

safety of the fleet. We have not changed this AD in this regard.

Request To Remove Requirement To Refer to This AD in Repair Approvals

    UAL requested that we remove the statement ``for a repair method to 
be approved, the repair approval must specifically refer to this AD'' 
in paragraph (i) of the proposed AD (79 FR 13925, March 12, 2014). UAL 
stated that this statement could have a significant impact on the 
financial cost and customer support between the operator and Airbus. 
UAL also stated that this statement should be removed for those general 
reasons stated in A4A's comment on the same topic in NPRM 2012-NM-101-
AD (78 FR 78285, December 26, 2013), which stated, among other 
justifications, that ``The added costs for this AD and all that may 
follow bearing the new procedural wording represent an unfair burden 
placed solely on U.S. registered aircraft.''
    We concur with the commenter's request to remove the requirement to 
include the AD reference in repair approvals. Since late 2006, we have 
included a standard paragraph titled ``Airworthy Product'' in all MCAI 
ADs in which the FAA develops an AD based on a foreign authority's AD. 
The MCAI or referenced service information in an FAA AD often directs 
the owner/operator to contact the manufacturer for corrective actions, 
such as a repair. Briefly, the Airworthy Product paragraph allowed 
owners/operators to use corrective actions provided by the manufacturer 
if those actions were FAA-approved. In addition, the paragraph stated 
that any actions approved by the State of Design Authority (or its 
delegated agent) are considered to be FAA-approved.
    In the NPRM (79 FR 13925, March 12, 2014), we proposed to prevent 
the use of repairs that were not specifically developed to correct the 
unsafe condition, by requiring that the repair approval provided by the 
State of Design Authority or its delegated agent specifically refer to 
this FAA AD. This change was 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 proposed to change the phrase ``its 
delegated agent'' to include ``the Design Approval Holder (DAH) with a 
State of Design Authority's design organization approval (DOA)'' to 
refer to a DAH authorized to approve required repairs for the AD.
    Comments were provided to the NPRM (79 FR 13925, March 12, 2014) 
and to an NPRM referenced by the commenter (i.e., Directorate 
Identifier 2012-NM-101-AD (78 FR 78285, December 26, 2013)) about these 
proposed changes. One commenter to the NPRM having Directorate 
Identifier 2012-NM-101-AD, United Parcel Service (UPS), stated the 
following: ``The proposed wording, being specific to repairs, 
eliminates the interpretation that Airbus messages are acceptable for 
approving minor deviations (corrective actions) needed during 
accomplishment of an AD mandated Airbus service bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed that paragraph and 
retitled it ``Contacting the Manufacturer.'' This paragraph now 
clarifies that for any requirement in this AD to obtain corrective 
actions from a manufacturer, the actions must be accomplished using a 
method approved by the FAA, EASA, or Airbus's EASA DOA.
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility afforded previously 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the AD Implementation 
Aviation Rulemaking Committee to increase flexibility in complying with 
ADs by identifying those actions in manufacturers' service instructions 
that are ``Required for Compliance'' with ADs. We continue to work with 
manufacturers to implement this recommendation. But once we determine 
that an action is required, any deviation from the requirement must be 
approved as an alternative method of compliance.
    Other commenters to NPRM 2012-NM-101-AD (78 FR 78285, December 26, 
2013) pointed out that in many cases the foreign manufacturer's service 
bulletin and the foreign authority's MCAI may have been issued some 
time before the FAA AD. Therefore, the DOA may have provided U.S. 
operators with an approved repair, developed with full awareness of the 
unsafe condition, before the FAA AD is issued. Under these 
circumstances, to comply with the FAA AD, the operator would be 
required to go back to the manufacturer's DOA and obtain a new approval 
document, adding time and expense to the compliance process with no 
safety benefit.
    Based on these comments, we removed the requirement from this AD 
that the DAH-provided repair specifically refer to this AD. Before 
adopting such a requirement in the future, the FAA will coordinate with 
affected DAHs and verify they are prepared to implement means to ensure 
that their repair approvals consider the unsafe condition addressed in 
an AD. Any such requirements will be adopted through the normal AD 
rulemaking process, including notice-and-comment procedures, when 
appropriate.
    We have also decided not to include a generic reference to either 
the ``delegated agent'' or the ``DAH with State of Design Authority 
design organization approval,'' but instead we will provide the 
specific delegation approval granted by the State of Design Authority 
for the DAH.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR

[[Page 11099]]

13925, March 12, 2014) for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 13925, March 12, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A320-53-1195, Revision 05, 
dated November 22, 2013, which describes procedures for inspections of 
the MLG door actuator fittings on the keel beam, and corrective actions 
if necessary. We also reviewed Airbus Service Bulletin A320-53-1196, 
Revision 04, dated November 22, 2013, which describes procedures for 
inspections of the MLG door hinge fitting on the keel beam, and 
corrective actions if necessary. This service information is reasonably 
available; see ADDRESSES for ways to access this service information.

Costs of Compliance

    We estimate that this 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 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 will take about 26 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this 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 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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:

2015-02-14 Airbus: Amendment 39-18081. Docket No. FAA-2014-0139; 
Directorate Identifier 2012-NM-133-AD.

(a) Effective Date

    This AD becomes effective April 6, 2015.

(b) Affected ADs

    This AD replaces 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 (MSNs).
    (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 cracking on the MLG 
door hinge fitting and actuator fitting on the keel beam, 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 11100]]

(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), with specific delegation approval language. For 
airplanes having serial numbers up to 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, where 
that service information specifies that the applicable corrective 
action is contacting Airbus, before further flight, repair using a 
method approved by the Manager, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA).
    (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, where that service information specifies 
that the applicable corrective action is contacting Airbus, before 
further flight, repair using a method approved by the Manager, ANM-
116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's 
EASA DOA.
    (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; 
as applicable; 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 Service Bulletin A320-53-1195, Revision 05, dated November 
22, 2013; 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 Airbus's EASA DOA. 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 described in Airbus Service Bulletin A320-53-1195, or Task 
533154-02-1 of the Airbus A318/A319/A320/A321 Airworthiness 
Limitations Section 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 Service Bulletin A320-53-1196, Revision 04, dated November 
22, 2013; 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 Airbus's EASA DOA. 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 described 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 Limitation 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; Airbus A318/A319/A320/A321 
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 
10, dated October 2009; or Airbus A318/A319/A320/A321 Airworthiness 
Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated 
September 2010. 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 Airworthiness Limitation Items (DT ALI), Revision 
01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness 
Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated 
October 2009; and Airbus A318/A319/A320/A321 Airworthiness 
Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated 
September 2010.

[[Page 11101]]

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i)(1) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A320-53-
1195, Revision 03, dated November 8, 2011; or Airbus Service 
Bulletin A320-53-1195, Revision 04, dated August 22, 2012; which are 
not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (i)(2) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A320-53-
1196, Revision 02, dated November 8, 2011; or Airbus Service 
Bulletin A320-53-1196, Revision 03, dated August 22, 2012; which are 
not incorporated by reference in 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: 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) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (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) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0118, dated July 4, 2012, 
for related information. You may examine the MCAI in the AD docket 
on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0139-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (o)(5) and (o)(6) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
April 6, 2015.
    (i) Airbus Service Bulletin A320-53-1195, Revision 05, dated 
November 22, 2013.
    (ii) Airbus Service Bulletin A320-53-1196, Revision 04, dated 
November 22, 2013.
    (4) The following service information was approved for IBR on 
November 3, 2009 (74 FR 49795, September 29, 2009).
    (i) Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, 
including Appendix 01, dated April 5, 2007.
    (ii) Airbus Mandatory Service Bulletin A320-53-1196, Revision 
01, including Appendix 01, dated November 29, 2006.
    (5) 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.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 4, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02692 Filed 2-27-15; 8:45 am]
BILLING CODE 4910-13-P