Airworthiness Directives; Airbus Airplanes, 57753-57757 [2014-22469]

Download as PDF Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations envelope, which could result in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement of Fuse Pins and Access Cover Assemblies Within 48 months after the effective date of this AD: Replace the fuse pins for the outboard aft upper spar and the access cover assemblies on struts Nos. 1 and 4, with new fuse pins and access cover assemblies, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2238, dated January 31, 2014. asabaliauskas on DSK5VPTVN1PROD with RULES (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 manager of the ACO, send it to the attention of the person identified in paragraph (i) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) If the service information contains steps that are labeled as RC (Required for Compliance), those steps must be done to comply with this AD; any steps that are not labeled as RC are recommended. Those steps that are not labeled as RC may be deviated from, done as part of other actions, or done using accepted methods different from those identified in the specified service information without obtaining approval of an AMOC, provided the steps labeled as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps labeled as RC require approval of an AMOC. (i) Related Information For more information about this AD, contact Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6513; fax: 425–917– 6590; email: narinder.luthra@faa.gov. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference VerDate Sep<11>2014 17:52 Sep 25, 2014 Jkt 232001 (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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin 747– 54A2238, dated January 31, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA 98057–3356. For information on the availability of this material at the FAA, call 425–227–1221. (5) 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 September 12, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–22468 Filed 9–25–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0291; Directorate Identifier 2013–NM–137–AD; Amendment 39–17972; AD 2014–19–04] 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) 2004–03– 19, which applies to certain Airbus Model A320–111, –211 and –231 series airplanes. AD 2004–03–19 required repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action if necessary. AD 2004–03–19 also provided for an optional terminating modification for the repetitive inspection requirements. This new AD requires accomplishing the modification by installing washers between the transition pick-up angle SUMMARY: PO 00000 Frm 00051 Fmt 4700 Sfmt 4700 57753 and the pin nuts, and doing related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability of AD 2004–03–19. This AD was prompted by a determination that the optional terminating modification must be required in order to address the unsafe condition. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel. DATES: This AD becomes effective October 31, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 15, 2004 (69 FR 5922, February 9, 2004). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0291; 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. 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 2004–03–19, Amendment 39–13463 (69 FR 5922, February 9, 2004). AD 2004–03–19 applied to certain Airbus Model A320– 111, –211, and –231 series airplanes. The NPRM published in the Federal Register on May 30, 2014 (79 FR 31057). The NPRM was prompted by a determination that the optional terminating modification must be E:\FR\FM\26SER1.SGM 26SER1 57754 Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations required in order to address the unsafe condition. The NPRM proposed to require repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action if necessary. The NPRM also proposed to require a terminating modification for the repetitive inspection requirements. The NPRM also proposed to add airplanes to the applicability. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0137, dated July 9, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A320–111, –211, and –231 series airplanes. The MCAI states: asabaliauskas on DSK5VPTVN1PROD with RULES During the A320 fatigue test campaign, it has been determined that fatigue damage could appear on the transition and pick-up angle between Frame (FR) 35 and FR36. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, ´ ´ DGAC [Direction Generale de l’Aviation Civile] France issued AD 2002–183 [related to FAA AD 2004–03–19, Amendment 39– 13463 (69 FR 5922, February 9, 2004)], to require repetitive inspections of the center fuselage pick-up angle between FR35 and FR36, below stringer 30, left hand (LH) and right hand (RH) sides, and, depending on findings, accomplishment of applicable corrective action(s). Since that [DGAC] AD [2002–183] was issued, a modification was developed, which has been published through Airbus Service Bulletin (SB) A320–53–1027 for in-service application, introducing additional washers below the riveting, which constitutes terminating action for the repetitive inspections. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 2002–183, which is superseded, and requires modification of the transition and pick-up angle between FR35 and FR36. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-02910002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 VerDate Sep<11>2014 17:52 Sep 25, 2014 Jkt 232001 FR 31057, May 30, 2014) or on the determination of the cost to the public. ‘‘Contacting the Manufacturer’’ Paragraph in this AD 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 11016, February 27, 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, for certain new requirements, we proposed to change the phrase ‘‘its delegated agent’’ to include a design approval holder (DAH) with State of Design Authority design organization approval (DOA), as applicable, to refer to a DAH authorized to approve required repairs for the proposed AD. No comments were provided to the NPRM (79 FR 11016, February 27, 2014) about these proposed changes. However, a comment was provided for an NPRM having Directorate Identifier 2012–NM– 101–AD (78 FR 78285, December 26, 2013). The commenter 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 PO 00000 Frm 00052 Fmt 4700 Sfmt 4700 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 the 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, the European Aviation Safety Agency (EASA), or Airbus’s EASA Design Organization Approval (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 previously afforded 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 Airworthiness Directive 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 the NPRM having Directorate Identifier 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 might E:\FR\FM\26SER1.SGM 26SER1 Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations have been issued some time before the FAA AD. Therefore, the DOA might 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 that the DAHprovided repair specifically refer to this AD. Before adopting such a requirement, the FAA will coordinate with affected DAHs and verify they are prepared to implement means to ensure 57755 that their repair approvals consider the unsafe condition addressed in this AD. Any such requirements will be adopted through the normal AD rulemaking process, including notice-and-comment procedures, when appropriate. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘DAH with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by EASA for the DAH. and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 31057, May 30, 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 31057, May 30, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Conclusion Costs of Compliance We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously We estimate that this AD affects 482 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection [retained action 9 work-hours × $85 per hour = from AD 2004–03–19, $765 per inspection cycle. Amendment 39–13463 (69 FR 5922, February 9, 2004)]. Inspection for Model A320–212 9 work-hours × $85 per hour = airplanes [new action]. $765 per inspection cycle. Terminating modification [new 28 work-hours × $85 per hour action]. = $2,380. Authority for This Rulemaking asabaliauskas on DSK5VPTVN1PROD with RULES 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 VerDate Sep<11>2014 17:52 Sep 25, 2014 Jkt 232001 Parts cost $0 $765 per inspection cycle ....... $18,360 per inspection cycle (24 airplanes). $0 $765 per inspection cycle ....... $1,837 $4,217 ..................................... $32,130 per inspection cycle (42 airplanes). $2,032,594. 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. 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0291; 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. PO 00000 Frm 00053 Cost on U.S. operators Cost per product Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2004–03–19, Amendment 39–13463 (69 FR 5922, February 9, 2004), and adding the following new AD: ■ 2014–19–04 Airbus: Amendment 39–17972. Docket No. FAA–2014–0291; Directorate Identifier 2013–NM–137–AD. (a) Effective Date This AD becomes effective October 31, 2014. E:\FR\FM\26SER1.SGM 26SER1 57756 Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations (b) Affected ADs This AD replaces AD 2004–03–19, Amendment 39–13463 (69 FR 5922, February 9, 2004). (c) Applicability This AD applies to Airbus Model A320– 111, –211, –212, and –231 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by the determination that the modification must be accomplished in order to address the unsafe condition. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel. asabaliauskas on DSK5VPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Detailed and Rotating Probe Inspections This paragraph restates the requirements of paragraph (b) of AD 2004–03–19, Amendment 39–13463 (69 FR 5922, February 9, 2004). For Model A320–111, –211, and –231 airplanes on which the modification specified in AD 98–12–18, Amendment 39– 10573 (63 FR 31345, June 9, 1998), has not been done: Do the applicable inspections specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1028, Revision 01, dated February 12, 2002. (1) For airplanes on which the inspections required by AD 98–12–18, Amendment 39– 10573 (63 FR 31345, June 9, 1998), have been done: Within 12,000 flight cycles after accomplishment of the last inspection required by AD 98–12–18, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking. (2) For airplanes on which the inspections required by AD 98–12–18, Amendment 39– 10573 (63 FR 31345, June 9, 1998), have not been done: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking. (i) Before the accumulation of 10,400 total flight cycles, or 24,600 total flight hours, whichever is first. (ii) Before the accumulation of 16,000 total flight cycles, or within 3,500 flight cycles after March 15, 2004 (the effective date of AD 2004–03–19, Amendment 39–13463 (69 FR 5922, February 9, 2004), whichever is first. (h) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (c) of AD 2004–03–19, VerDate Sep<11>2014 17:52 Sep 25, 2014 Jkt 232001 Amendment 39–13463 (69 FR 5922, February 9, 2004). For Model A320–111, –211, and –231 airplanes: Repeat the detailed and rotating probe inspections specified in paragraphs (g)(1) and (g)(2) of this AD at intervals not to exceed 10,400 flight cycles or 24,600 flight hours, whichever is first, until the modification specified in paragraph (m) of this AD has been done. (i) Retained Corrective Action for Paragraphs (g) and (h) of This AD This paragraph restates the requirements of paragraph (d) of AD 2004–03–19, Amendment 39–13463 (69 FR 5922, February 9, 2004), with specific delegation approval language. For Model A320–111, –211, and –231 airplanes: If any cracking is found during any inspection required by paragraph (g) or (h) of this AD, prior to further flight, either repair the cracking per the Accomplishment Instructions of Airbus Service Bulletin A320–53–1028, Revision 01, dated February 12, 2002; or do the modification specified in paragraph (m) of this AD. Where Airbus Service Bulletin A320–53–1028, Revision 01, dated February 12, 2002, specifies to contact the manufacturer for repair instructions, prior to further flight, repair the cracking in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization ´ ´ Approval (DOA); or the Direction Generale de l’Aviation Civile (or its delegated agent). If the cracking is repaired, repeat the inspections as required by paragraph (h) of this AD. (j) New Detailed and Rotating Probe Inspections for Model A320–212 Airplanes For Model A320–212 airplanes on which the modification specified in Airbus Service Bulletin A320–53–1027 has not been done as of the effective date of this AD: Do the applicable inspections specified in paragraph (j)(1) or (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1028, Revision 01, dated February 12, 2002. (1) For airplanes on which the inspections specified in Airbus Service Bulletin A320– 53–1028 have been done as of the effective date of this AD: At the later of the times specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking. (i) Within 10,400 flight cycles or 24,600 flight hours, whichever occurs first after accomplishing the most recent inspection specified in Airbus Service Bulletin A320– 53–1028. (ii) Within 90 days after the effective date of this AD. (2) For airplanes on which the inspections specified in Airbus Service Bulletin A320– 53–1028 have not been done as of the effective date of this AD: At the later of the times specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking. PO 00000 Frm 00054 Fmt 4700 Sfmt 4700 (i) Before the accumulation of 10,400 total flight cycles, or 24,600 total flight hours, whichever occurs first. (ii) Within 90 days after the effective date of this AD. (k) New Repetitive Inspections for Model A320–212 Airplanes For Model A320–212 airplanes: Repeat the detailed and rotating probe inspections specified in paragraphs (j)(1) and (j)(2) of this AD at intervals not to exceed 10,400 flight cycles or 24,600 flight hours, whichever occurs first, until the modification specified in paragraph (m) of this AD has been done. (l) New Corrective Action for Model A320– 212 Airplanes For Model A320–212 airplanes: If any cracking is found during any inspection required by paragraph (j) or (k) of this AD, before further flight, do the actions specified in either paragraph (l)(1) or (l)(2) of this AD. (1) Repair the crack in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1028, Revision 01, dated February 12, 2002, except where Airbus Service Bulletin A320–53–1028, Revision 01, dated February 12, 2002, specifies to contact the manufacturer, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). After the cracking is repaired, repeat the inspections required by paragraph (k) of this AD. (2) Do the modification specified in paragraph (m) of this AD. (m) New Terminating Modification for All Airplanes For all airplanes: Before the accumulation of 40,000 flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later, but not exceeding 48,000 flight cycles since first flight, modify by doing rotating probe inspections for cracking of certain fastener holes, replacing transition angles if any cracking is found in the transition angles, repairing if any pick-up angles cracking is found, and installing washers between the transition pick-up angle and the pin nuts; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1027, Revision 03, dated February 12, 2002, except where Airbus Service Bulletin A320–53–1027, Revision 03, dated February 12, 2001, specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Accomplishment of this modification terminates the repetitive inspections required by paragraphs (h) and (k) of this AD. (n) Terminating Modification For airplanes on which Airbus Modification 21202 has been embodied in production: No actions are required by this AD. E:\FR\FM\26SER1.SGM 26SER1 Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations asabaliauskas on DSK5VPTVN1PROD with RULES (o) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1028, dated March 1, 1994, which was incorporated by reference in AD 98–12–18, Amendment 39–10573 (63 FR 31345, June 9, 1998). (2) This paragraph provides credit for the action specified in paragraph (m) of this AD, if that action was performed before the effective date of this AD using the service information specified in paragraph (o)(2)(i), (o)(2)(ii), or (o)(2)(iii) of this AD, which is not incorporated by reference in this AD. (i) Airbus Service Bulletin A320–53–1027, dated March 1, 1994. (ii) Airbus Service Bulletin A320–53–1027, Revision 1, dated September 5, 1994. (iii) Airbus Service Bulletin A320–53– 1027, Revision 2, dated June 8, 1995 (which was incorporated by reference in AD 98–12– 18, Amendment 39–10573 (63 FR 31345, June 9, 1998)). (p) 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. (i) 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. (ii) AMOCs approved previously in accordance with AD 2004–03–19, Amendment 39–13463 (69 FR 5922, February 9, 2004), are approved as AMOCs for the corresponding provisions of 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 the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness VerDate Sep<11>2014 17:52 Sep 25, 2014 Jkt 232001 Directive 2013–0137, dated July 9, 2013, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0291-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (r)(4) and (r)(5) of this AD. (r) 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 March 15, 2004 (69 FR 5922, February 9, 2004). (i) Airbus Service Bulletin A320–53–1027, Revision 03, dated February 12, 2002. (ii) Airbus Service Bulletin A320–53–1028, Revision 01, dated February 12, 2002. (4) 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. (5) 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. (6) 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 September 12, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. 57757 Tri-Area Class B airspace area to include exclusion of restricted area R–4001C from the Class B airspace when the restricted area is active. The remainder of the Class B description is not affected by this change. DATES: Effective date: 0901 UTC September 26, 2014. The Director of the Federal Register approves this incorporation by reference action under 1 CFR part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. ADDRESSES: FAA Order 7400.9Y, Airspace Designations and Reporting Points, and subsequent amendments can be viewed online at http://www.faa.gov/ air_traffic/publications/. The Order is also available for inspection 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://archives.gov/federal_ register/code_of_federal-regulations/ibr_ locations.html. FAA Order 7400.9, Airspace Designations and Reporting Points, is published yearly and effective on September 15. For further information, you can contact the Airspace Policy and Regulations Group, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: 202–267–8783. FOR FURTHER INFORMATION CONTACT: Paul Gallant, Airspace Policy and Regulations Group, Office of Airspace Services, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: AGENCY: Background On May 23, 2014, the FAA published a final rule establishing restricted area R–4001C at Aberdeen Proving Ground, MD (79 FR 29661). R–4001C was formed by further subdividing small sections of existing restricted areas R–4001A and R–4001B that currently extend into Area D of the Washington, DC, Tri-Area Class B airspace area. The description of Area D excludes the airspace in restricted areas R–4001A and B from the Class B airspace. This change simply updates that description to add R–4001C (which is imbedded within R–4001A and R– 4001B) to the exclusionary language. Aeronautical charts have been updated to reflect this information. This action amends the description of Area D of the Washington The Rule The FAA is amending Title 14 Code of Federal Regulations (14 CFR) part 71 to update the description of Area D in the Washington Tri-Area Class B [FR Doc. 2014–22469 Filed 9–25–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2014–0713; Airspace Docket No. 14–AWA–1] RIN 2120–AA66 Amendment of Class B Airspace; Washington Tri-Area, DC Federal Aviation Administration (FAA), DOT. ACTION: Final rule; technical amendment. SUMMARY: PO 00000 Frm 00055 Fmt 4700 Sfmt 4700 E:\FR\FM\26SER1.SGM 26SER1

Agencies

[Federal Register Volume 79, Number 187 (Friday, September 26, 2014)]
[Rules and Regulations]
[Pages 57753-57757]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-22469]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0291; Directorate Identifier 2013-NM-137-AD; 
Amendment 39-17972; AD 2014-19-04]
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) 2004-03-19, 
which applies to certain Airbus Model A320-111, -211 and -231 series 
airplanes. AD 2004-03-19 required repetitive inspections for cracking 
in the transition and pick-up angles in the lower part of the center 
fuselage area, and corrective action if necessary. AD 2004-03-19 also 
provided for an optional terminating modification for the repetitive 
inspection requirements. This new AD requires accomplishing the 
modification by installing washers between the transition pick-up angle 
and the pin nuts, and doing related investigative and corrective 
actions if necessary. This new AD also adds airplanes to the 
applicability of AD 2004-03-19. This AD was prompted by a determination 
that the optional terminating modification must be required in order to 
address the unsafe condition. We are issuing this AD to prevent fatigue 
cracking in the transition and pick-up angles of the lower part of the 
center fuselage, which could result in reduced structural integrity of 
the wing-fuselage support and fuselage pressure vessel.

DATES: This AD becomes effective October 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 15, 
2004 (69 FR 5922, February 9, 2004).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0291; 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.

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 2004-03-19, Amendment 39-13463 (69 FR 5922, 
February 9, 2004). AD 2004-03-19 applied to certain Airbus Model A320-
111, -211, and -231 series airplanes. The NPRM published in the Federal 
Register on May 30, 2014 (79 FR 31057). The NPRM was prompted by a 
determination that the optional terminating modification must be

[[Page 57754]]

required in order to address the unsafe condition. The NPRM proposed to 
require repetitive inspections for cracking in the transition and pick-
up angles in the lower part of the center fuselage area, and corrective 
action if necessary. The NPRM also proposed to require a terminating 
modification for the repetitive inspection requirements. The NPRM also 
proposed to add airplanes to the applicability. We are issuing this AD 
to prevent fatigue cracking in the transition and pick-up angles of the 
lower part of the center fuselage, which could result in reduced 
structural integrity of the wing-fuselage support and fuselage pressure 
vessel.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0137, dated July 9, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A320-111, -211, and -231 series airplanes. The MCAI states:

    During the A320 fatigue test campaign, it has been determined 
that fatigue damage could appear on the transition and pick-up angle 
between Frame (FR) 35 and FR36.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2002-
183 [related to FAA AD 2004-03-19, Amendment 39-13463 (69 FR 5922, 
February 9, 2004)], to require repetitive inspections of the center 
fuselage pick-up angle between FR35 and FR36, below stringer 30, 
left hand (LH) and right hand (RH) sides, and, depending on 
findings, accomplishment of applicable corrective action(s).
    Since that [DGAC] AD [2002-183] was issued, a modification was 
developed, which has been published through Airbus Service Bulletin 
(SB) A320-53-1027 for in-service application, introducing additional 
washers below the riveting, which constitutes terminating action for 
the repetitive inspections.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 2002-183, which is superseded, and 
requires modification of the transition and pick-up angle between 
FR35 and FR36.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0291-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 31057, May 30, 
2014) or on the determination of the cost to the public.

``Contacting the Manufacturer'' Paragraph in this AD

    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 11016, February 27, 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, for certain new 
requirements, we proposed to change the phrase ``its delegated agent'' 
to include a design approval holder (DAH) with State of Design 
Authority design organization approval (DOA), as applicable, to refer 
to a DAH authorized to approve required repairs for the proposed AD.
    No comments were provided to the NPRM (79 FR 11016, February 27, 
2014) about these proposed changes. However, a comment was provided for 
an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285, 
December 26, 2013). The commenter 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 the 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, the European Aviation Safety Agency (EASA), or Airbus's 
EASA Design Organization Approval (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 previously afforded 
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 Airworthiness 
Directive 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 the NPRM having Directorate Identifier 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 might

[[Page 57755]]

have been issued some time before the FAA AD. Therefore, the DOA might 
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 that the DAH-
provided repair specifically refer to this AD. Before adopting such a 
requirement, 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 this AD. Any such 
requirements will be adopted through the normal AD rulemaking process, 
including notice-and-comment procedures, when appropriate.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``DAH with State of Design Authority design 
organization approval,'' but instead we have provided the specific 
delegation approval granted by EASA for the DAH.

Conclusion

    We reviewed the relevant data 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 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 31057, May 30, 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 31057, May 30, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 482 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection [retained action from   9 work-hours x $85             $0  $765 per inspection   $18,360 per
 AD 2004-03-19, Amendment 39-       per hour = $765 per                cycle.                inspection cycle
 13463 (69 FR 5922, February 9,     inspection cycle.                                        (24 airplanes).
 2004)].
Inspection for Model A320-212      9 work-hours x $85             $0  $765 per inspection   $32,130 per
 airplanes [new action].            per hour = $765 per                cycle.                inspection cycle
                                    inspection cycle.                                        (42 airplanes).
Terminating modification [new      28 work-hours x $85        $1,837  $4,217..............  $2,032,594.
 action].                           per hour = $2,380.
----------------------------------------------------------------------------------------------------------------

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-2014-0291; 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) 
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), and 
adding the following new AD:

2014-19-04 Airbus: Amendment 39-17972. Docket No. FAA-2014-0291; 
Directorate Identifier 2013-NM-137-AD.

(a) Effective Date

    This AD becomes effective October 31, 2014.

[[Page 57756]]

(b) Affected ADs

    This AD replaces AD 2004-03-19, Amendment 39-13463 (69 FR 5922, 
February 9, 2004).

(c) Applicability

    This AD applies to Airbus Model A320-111, -211, -212, and -231 
airplanes, certificated in any category, all manufacturer serial 
numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by the determination that the modification 
must be accomplished in order to address the unsafe condition. We 
are issuing this AD to prevent fatigue cracking in the transition 
and pick-up angles of the lower part of the center fuselage, which 
could result in reduced structural integrity of the wing-fuselage 
support and fuselage pressure vessel.

(f) Compliance

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

(g) Retained Detailed and Rotating Probe Inspections

    This paragraph restates the requirements of paragraph (b) of AD 
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For 
Model A320-111, -211, and -231 airplanes on which the modification 
specified in AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 
1998), has not been done: Do the applicable inspections specified in 
paragraphs (g)(1) and (g)(2) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, 
Revision 01, dated February 12, 2002.
    (1) For airplanes on which the inspections required by AD 98-12-
18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have been done: 
Within 12,000 flight cycles after accomplishment of the last 
inspection required by AD 98-12-18, do a detailed inspection of the 
transition angle and a rotating probe inspection of the pick-up 
angle in the lower part of the center fuselage area for cracking.
    (2) For airplanes on which the inspections required by AD 98-12-
18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have not been 
done: At the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD, do a detailed inspection of the 
transition angle and a rotating probe inspection of the pick-up 
angle in the lower part of the center fuselage area for cracking.
    (i) Before the accumulation of 10,400 total flight cycles, or 
24,600 total flight hours, whichever is first.
    (ii) Before the accumulation of 16,000 total flight cycles, or 
within 3,500 flight cycles after March 15, 2004 (the effective date 
of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), 
whichever is first.

(h) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (c) of AD 
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For 
Model A320-111, -211, and -231 airplanes: Repeat the detailed and 
rotating probe inspections specified in paragraphs (g)(1) and (g)(2) 
of this AD at intervals not to exceed 10,400 flight cycles or 24,600 
flight hours, whichever is first, until the modification specified 
in paragraph (m) of this AD has been done.

(i) Retained Corrective Action for Paragraphs (g) and (h) of This AD

    This paragraph restates the requirements of paragraph (d) of AD 
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), with 
specific delegation approval language. For Model A320-111, -211, and 
-231 airplanes: If any cracking is found during any inspection 
required by paragraph (g) or (h) of this AD, prior to further 
flight, either repair the cracking per the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1028, Revision 01, 
dated February 12, 2002; or do the modification specified in 
paragraph (m) of this AD. Where Airbus Service Bulletin A320-53-
1028, Revision 01, dated February 12, 2002, specifies to contact the 
manufacturer for repair instructions, prior to further flight, 
repair the cracking in accordance with a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA); or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated 
agent). If the cracking is repaired, repeat the inspections as 
required by paragraph (h) of this AD.

(j) New Detailed and Rotating Probe Inspections for Model A320-212 
Airplanes

    For Model A320-212 airplanes on which the modification specified 
in Airbus Service Bulletin A320-53-1027 has not been done as of the 
effective date of this AD: Do the applicable inspections specified 
in paragraph (j)(1) or (j)(2) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, 
Revision 01, dated February 12, 2002.
    (1) For airplanes on which the inspections specified in Airbus 
Service Bulletin A320-53-1028 have been done as of the effective 
date of this AD: At the later of the times specified in paragraphs 
(j)(1)(i) and (j)(1)(ii) of this AD, do a detailed inspection of the 
transition angle and a rotating probe inspection of the pick-up 
angle in the lower part of the center fuselage area for cracking.
    (i) Within 10,400 flight cycles or 24,600 flight hours, 
whichever occurs first after accomplishing the most recent 
inspection specified in Airbus Service Bulletin A320-53-1028.
    (ii) Within 90 days after the effective date of this AD.
    (2) For airplanes on which the inspections specified in Airbus 
Service Bulletin A320-53-1028 have not been done as of the effective 
date of this AD: At the later of the times specified in paragraphs 
(j)(2)(i) and (j)(2)(ii) of this AD, do a detailed inspection of the 
transition angle and a rotating probe inspection of the pick-up 
angle in the lower part of the center fuselage area for cracking.
    (i) Before the accumulation of 10,400 total flight cycles, or 
24,600 total flight hours, whichever occurs first.
    (ii) Within 90 days after the effective date of this AD.

(k) New Repetitive Inspections for Model A320-212 Airplanes

    For Model A320-212 airplanes: Repeat the detailed and rotating 
probe inspections specified in paragraphs (j)(1) and (j)(2) of this 
AD at intervals not to exceed 10,400 flight cycles or 24,600 flight 
hours, whichever occurs first, until the modification specified in 
paragraph (m) of this AD has been done.

(l) New Corrective Action for Model A320-212 Airplanes

    For Model A320-212 airplanes: If any cracking is found during 
any inspection required by paragraph (j) or (k) of this AD, before 
further flight, do the actions specified in either paragraph (l)(1) 
or (l)(2) of this AD.
    (1) Repair the crack in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1028, Revision 01, 
dated February 12, 2002, except where Airbus Service Bulletin A320-
53-1028, Revision 01, dated February 12, 2002, specifies to contact 
the manufacturer, before further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). After 
the cracking is repaired, repeat the inspections required by 
paragraph (k) of this AD.
    (2) Do the modification specified in paragraph (m) of this AD.

(m) New Terminating Modification for All Airplanes

    For all airplanes: Before the accumulation of 40,000 flight 
cycles since first flight, or within 1,500 flight cycles after the 
effective date of this AD, whichever occurs later, but not exceeding 
48,000 flight cycles since first flight, modify by doing rotating 
probe inspections for cracking of certain fastener holes, replacing 
transition angles if any cracking is found in the transition angles, 
repairing if any pick-up angles cracking is found, and installing 
washers between the transition pick-up angle and the pin nuts; in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1027, Revision 03, dated February 12, 2002, except 
where Airbus Service Bulletin A320-53-1027, Revision 03, dated 
February 12, 2001, specifies to contact Airbus, before further 
flight, repair using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). Accomplishment of this modification 
terminates the repetitive inspections required by paragraphs (h) and 
(k) of this AD.

(n) Terminating Modification

    For airplanes on which Airbus Modification 21202 has been 
embodied in production: No actions are required by this AD.

[[Page 57757]]

(o) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1028, dated March 1, 1994, which was incorporated by reference in AD 
98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998).
    (2) This paragraph provides credit for the action specified in 
paragraph (m) of this AD, if that action was performed before the 
effective date of this AD using the service information specified in 
paragraph (o)(2)(i), (o)(2)(ii), or (o)(2)(iii) of this AD, which is 
not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A320-53-1027, dated March 1, 1994.
    (ii) Airbus Service Bulletin A320-53-1027, Revision 1, dated 
September 5, 1994.
    (iii) Airbus Service Bulletin A320-53-1027, Revision 2, dated 
June 8, 1995 (which was incorporated by reference in AD 98-12-18, 
Amendment 39-10573 (63 FR 31345, June 9, 1998)).

(p) 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.
    (i) 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.
    (ii) AMOCs approved previously in accordance with AD 2004-03-19, 
Amendment 39-13463 (69 FR 5922, February 9, 2004), are approved as 
AMOCs for the corresponding provisions of 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 the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0137, dated July 9, 2013, for related information. You may examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0291-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (r)(4) and (r)(5) of this AD.

(r) 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 
March 15, 2004 (69 FR 5922, February 9, 2004).
    (i) Airbus Service Bulletin A320-53-1027, Revision 03, dated 
February 12, 2002.
    (ii) Airbus Service Bulletin A320-53-1028, Revision 01, dated 
February 12, 2002.
    (4) 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.
    (5) 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.
    (6) 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 September 12, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-22469 Filed 9-25-14; 8:45 am]
BILLING CODE 4910-13-P