Airworthiness Directives; Airbus Airplanes, 29198-29202 [2016-10914]

Download as PDF 29198 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules (h) Retained Provision Regarding Alternative Actions, Intervals With Updated Information This paragraph restates the requirements of paragraph (i) of AD 2007–11–13, with updated information. Except as required by paragraph (i) of this AD: After the ALS has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, may be used unless the actions, intervals, are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD. (i) New Maintenance or Inspection Program Revision Within 180 days after the effective date of this AD: Revise the maintenance or inspection program, as applicable, to incorporate the information specified in Boeing 717–200 ALI, Report MDC–96K9063, Revision 14, dated July 2015. The initial compliance times for doing the actions specified in Boeing 717–200 ALI, Report MDC–96K9063, Revision 14, dated July 2015, are at the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD. Compliance with this paragraph terminates the requirements of paragraph (g) of this AD. (1) Within the applicable compliance times specified in Boeing 717–200 ALI, Report MDC–96K9063, Revision 14, dated July 2015. (2) Within 180 days from the effective date of this AD. mstockstill on DSK3G9T082PROD with PROPOSALS (j) No Alternative Actions or Intervals After the maintenance or inspection program has been revised as required by paragraph (i) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (k) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (l)(1) of this AD. (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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 (4) AMOCs approved previously for AD 2007–11–13 are not approved as AMOCs with this AD. (l) Related Information (1) For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5348; fax: 562–627–5210; email: eric.schrieber@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https:// www.myboeingfleet.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on April 28, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–10740 Filed 5–10–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6429; Directorate Identifier 2015–NM–117–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2015–05– 02, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015–05–02 requires revising the maintenance or inspection program to incorporate new, more restrictive airworthiness limitations. Since we issued AD 2015–05–02, an evaluation by the design approval holder (DAH) indicates that principal structural elements and certain life limited parts are subject to widespread fatigue damage (WFD). This proposed AD would require revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. We are proposing this AD to prevent fatigue SUMMARY: PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane. We must receive comments on this proposed AD by June 27, 2016. DATES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 https://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. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6429; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: E:\FR\FM\11MYP1.SGM 11MYP1 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–6429; Directorate Identifier 2015–NM–117–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. mstockstill on DSK3G9T082PROD with PROPOSALS Discussion Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-sitedamage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as widespread fatigue damage (WFD). As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. On February 25, 2015, we issued AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015) (‘‘AD 2015– 05–02’’) to supersede AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015). AD 2015–05–02 requires revising the maintenance or inspection program, as applicable, to incorporate new, more restrictive airworthiness limitations on all Airbus Model A318, A319, A320, and A321 series airplanes. Since we issued AD 2015–05–02, an evaluation by the DAH indicates that principal structural elements and certain life limited parts are subject to widespread fatigue damage WFD. This proposed AD would require revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0083, dated May 12, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition. The MCAI states: The airworthiness limitations for Airbus A320 family aeroplanes are currently PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 29199 included in Airbus A318/A319/A320/A321 Airworthiness Limitations Section (hereafter referred to as ‘ALS’) documents. The Damage Tolerant airworthiness limitation items are published in ALS Part 2, approved by EASA. The instructions contained in the ALS Part 2 have been identified as mandatory actions for continued airworthiness. Failure to comply with these instructions could result in an unsafe condition. Previously, EASA issued AD 2013–0147 (https://ad.easa.europa.eu/blob/easa_ad_ 2013_0147_superseded.pdf/AD_20130147_1) [which corresponds to FAA AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015) to require accomplishment of all maintenance tasks as described in ALS Part 2 at Revision 02. The new ALS Part 2 Revision 03 [Issue October 27, 2014] includes new and/or more restrictive items and was approved on 27 October 2014. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2013–0147, which is superseded, and requires accomplishment of all maintenance tasks as described in ALS Part 2 at Revision 03. The required action is revising the maintenance or inspection program to incorporate new or revised structural inspection requirements. The unsafe condition is fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6429. Other Relevant Rulemaking We have issued NPRM Docket FAA– 2015–6539, Directorate Identifier 2015– NM–036–AD (80 FR 74723, November 30, 2015), for all Airbus Model A318– 111 and –112 airplanes; Model A319– 111, –112, –113, –114, and –115 airplanes; Model A320–211, –212, and –214 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes. That NPRM proposes to require repetitive inspections that reduce the compliance time for Task 712111–01, Detailed Inspection of Forward Engine Mount Installation. Therefore, Task 712111–01 is not included in this proposed AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 04, dated December 18, 2015, of the A318/A319/A320/A321 Airworthiness Limitation Section (ALS). The service information describes DT ALIs associated with WFD. Airbus has also issued Part 2, Damage Tolerant Airworthiness Limitation Items E:\FR\FM\11MYP1.SGM 11MYP1 29200 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules (DT–ALI), Variation 4.2, dated January 15, 2016, of the A318/A319/A320/A321 Airworthiness Limitation Section (ALS). The service information describes DT ALIs associated with WFD. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. mstockstill on DSK3G9T082PROD with PROPOSALS FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. This proposed AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator might not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) in accordance with the provisions of paragraph (k)(1) of this proposed AD. The request should include a description of changes to the required actions that will ensure the continued damage tolerance of the affected structure. Differences Between This Proposed AD and the MCAI or Service Information This proposed AD differs from the MCAI in that it specifies revising the maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/ A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT– ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/ A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT– ALI), Variation 4.2, dated January 15, 2016. The MCAI specifies incorporating the ALIs specified in Airbus A318/ A319/A320/A321 ALS Safe Life Airworthiness Limitation Section (ALS), Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 03, VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 Issue October 27, 2014. We have coordinated this change with EASA. EASA has issued EASA Proposed Airworthiness Directive (PAD) 16–029, dated February 24, 2016, which specifies incorporating the ALI’s in Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 4.2, dated January 15, 2016. The MCAI specifies that if there are findings from the ALS inspection tasks, corrective actions must be accomplished in accordance with Airbus maintenance documentation. However, this proposed AD does not include that requirement. Operators of U.S.-registered airplanes are required by general airworthiness and operational regulations to perform maintenance using methods that are acceptable to the FAA. We consider those methods to be adequate to address any corrective actions necessitated by the findings of ALS inspections required by this proposed AD. Airworthiness Limitations Based on Type Design The FAA recently became aware of an issue related to the applicability of ADs that require incorporation of an ALS revision into an operator’s maintenance or inspection program. Typically, when these types of ADs are issued by civil aviation authorities of other countries, they apply to all airplanes covered under an identified type certificate (TC). The corresponding FAA AD typically retains applicability to all of those airplanes. In addition, U.S. operators must operate their airplanes in an airworthy condition, in accordance with 14 CFR 91.7(a). Included in this obligation is the requirement to perform any maintenance or inspections specified in the ALS, and in accordance with the ALS as specified in 14 CFR 43.16 and 91.403(c), unless an alternative has been approved by the FAA. When a type certificate is issued for a type design, the specific ALS, including revisions, is a part of that type design, as specified in 14 CFR 21.31(c). The sum effect of these operational and maintenance requirements is an obligation to comply with the ALS defined in the type design referenced in the manufacturer’s conformity statement. This obligation may introduce a conflict with an AD that requires a specific ALS revision if new airplanes are delivered with a later revision as part of their type design. PO 00000 Frm 00032 Fmt 4702 Sfmt 4702 To address this conflict, the FAA has approved AMOCs that allow operators to incorporate the most recent ALS revision into their maintenance/ inspection programs, in lieu of the ALS revision required by the AD. This eliminates the conflict and enables the operator to comply with both the AD and the type design. However, compliance with AMOCs is normally optional, and we recently became aware that some operators choose to retain the AD-mandated ALS revision in their fleet-wide maintenance/inspection programs, including those for new airplanes delivered with later ALS revisions, to help standardize the maintenance of the fleet. To ensure that operators comply with the applicable ALS revision for newly delivered airplanes containing a later revision than that specified in an AD, we plan to limit the applicability of ADs that mandate ALS revisions to those airplanes that are subject to an earlier revision of the ALS, either as part of the type design or as mandated by an earlier AD. This proposed AD therefore applies to the airplanes identified in paragraph (c) of this proposed AD with an original certificate of airworthiness or original export certificate of airworthiness that was issued on or before the date of approval of the ALS revision identified in this proposed AD. Operators of airplanes with an original certificate of airworthiness or original export certificate of airworthiness issued after that date must comply with the airworthiness limitations specified as part of the approved type design and referenced on the type certificate data sheet. Record of Ex Parte Communication In preparation of AD actions, it is the practice of the FAA to obtain technical information and information on the operational and economic impact from design approval holders and aircraft operators. We discussed certain issues related to this NPRM in a recent meeting with Airlines for America (A4A). Shortly after this NPRM is published, we will post a summary of this meeting in the rulemaking docket. For information on locating the docket, see ‘‘Examining the AD Docket.’’ Costs of Compliance We estimate that this proposed AD affects 959 airplanes of U.S. registry. The actions required by AD 2015–05– 02, and retained in this proposed AD take about 2 work-hours per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the actions that are E:\FR\FM\11MYP1.SGM 11MYP1 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules required by AD 2015–05–02 is $170 per product. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $163,030, or $170 per product. mstockstill on DSK3G9T082PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015), and adding the following new AD: ■ Airbus: Docket No. FAA–2016–6429; Directorate Identifier 2015–NM–117–AD. (a) Comments Due Date We must receive comments by June 27, 2016. (b) Affected ADs This AD replaces AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015) (‘‘AD 2015–05–02’’). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, with an original certificate of airworthiness or original export certificate of airworthiness issued on or before January 15, 2016. (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 05, Periodic Inspections. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) which indicates that principal structural elements and certain life limited parts are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Maintenance or Inspection Program Revision, With No Changes This paragraph restates the requirements of paragraph (n) of AD 2015–05–02, with no changes. Within 30 days after March 2, 2015 (the effective date of AD 2014–23–15, Amendment 39–18031 (80 FR 3871, January 26, 2015) (‘‘AD 2014–23–15’’)), revise the maintenance or inspection program, as applicable, to incorporate the Airworthiness PO 00000 Frm 00033 Fmt 4702 Sfmt 4702 29201 Limitation Items (ALIs) specified in paragraphs (g)(1) and (g)(2) of this AD. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in paragraphs (g)(1) and (g)(2) of this AD; or within 4 months after March 2, 2015 (the effective date of AD 2014– 23–15); whichever occurs later. (1) Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011. (2) Airbus A318/A319/A320/A321 ALS Part 2—Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013. (h) Retained Limitation: No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs), With Exception This paragraph restates the requirements of paragraph (o) of AD 2015–05–02, with an exception. Except as required by paragraph (i) of this AD, after accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k)(1) of this AD. (i) New Requirement of This AD: Maintenance or Inspection Program Revision Within 60 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/ A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 4.2, dated January 15, 2016. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT–ALI), Variation 4.2, dated January 15, 2016; without exceeding the inspection intervals in the ALIs specified in the service information identified in paragraph (g)(2) of this AD, except for the ALI tasks identified in paragraphs (i)(1) though (i)(4) of this AD. Accomplishing these actions terminates the requirements of paragraph (g)(2) of this AD. (1) Task 712111–01–1, ‘‘Detailed Inspection of Forward Engine Mount Installation.’’ (2) Task 712111–01–2, ‘‘Detailed Inspection of Forward Engine Mount Installation.’’ (3) Task 712111–01–3, ‘‘Detailed Inspection of Forward Engine Mount Installation.’’ (4) Task 712111–01–4, ‘‘Detailed Inspection of Forward Engine Mount Installation.’’ E:\FR\FM\11MYP1.SGM 11MYP1 29202 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules Issued in Renton, Washington, on May 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (k) 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 for AD 2015–05–02, are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) 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. mstockstill on DSK3G9T082PROD with PROPOSALS (j) New No Alternative Actions and/or Intervals After accomplishing the revision required by paragraph (i) of this AD, no alternative actions (e.g., inspections) and/or intervals may be used unless the actions and/or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (k)(1) of this AD. DEPARTMENT OF TRANSPORTATION (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0083, dated May 12, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2016–6429. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 [FR Doc. 2016–10914 Filed 5–10–16; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6430; Directorate Identifier 2015–NM–176–AD;] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2005–13– 30, which applies to all Boeing Model 737–100, –200, and –200C series airplanes. AD 2005–13–30 currently requires repetitive inspections to detect discrepancies of certain fuselage skin panels located just aft of the wheel well, and repair if necessary. Since we issued AD 2005–13–30, an evaluation by the design approval holder (DAH) indicates that the fuselage skin is subject to widespread fatigue damage (WFD), and we have received reports of cracks at the chem-milled steps in the fuselage skin. This proposed AD would add new fuselage skin inspections for cracking, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. We are proposing this AD to detect and correct fatigue cracking of the fuselage skin panels, which could cause rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by June 27, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. SUMMARY: PO 00000 Frm 00034 Fmt 4702 Sfmt 4702 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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. 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6430. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6430; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6430; fax: 425–917–6590; email: wade.sullivan@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–6430; Directorate Identifier 2015–NM–176–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// E:\FR\FM\11MYP1.SGM 11MYP1

Agencies

[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)]
[Proposed Rules]
[Pages 29198-29202]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10914]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6429; Directorate Identifier 2015-NM-117-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-05-
02, for certain Airbus Model A318, A319, A320, and A321 series 
airplanes. AD 2015-05-02 requires revising the maintenance or 
inspection program to incorporate new, more restrictive airworthiness 
limitations. Since we issued AD 2015-05-02, an evaluation by the design 
approval holder (DAH) indicates that principal structural elements and 
certain life limited parts are subject to widespread fatigue damage 
(WFD). This proposed AD would require revising the maintenance or 
inspection program, as applicable, to incorporate new or revised 
structural inspection requirements. We are proposing this AD to prevent 
fatigue cracking, accidental damage, or corrosion in principal 
structural elements, and WFD, which could result in reduced structural 
integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 27, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 https://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6429; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

[[Page 29199]]

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6429; 
Directorate Identifier 2015-NM-117-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as 
widespread fatigue damage (WFD). As an airplane ages, WFD will likely 
occur, and will certainly occur if the airplane is operated long enough 
without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    On February 25, 2015, we issued AD 2015-05-02, Amendment 39-18112 
(80 FR 15152, March 23, 2015) (``AD 2015-05-02'') to supersede AD 2014-
23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015). AD 2015-05-02 
requires revising the maintenance or inspection program, as applicable, 
to incorporate new, more restrictive airworthiness limitations on all 
Airbus Model A318, A319, A320, and A321 series airplanes.
    Since we issued AD 2015-05-02, an evaluation by the DAH indicates 
that principal structural elements and certain life limited parts are 
subject to widespread fatigue damage WFD. This proposed AD would 
require revising the maintenance or inspection program, as applicable, 
to incorporate new or revised structural inspection requirements.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0083, dated May 12, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition.
    The MCAI states:

    The airworthiness limitations for Airbus A320 family aeroplanes 
are currently included in Airbus A318/A319/A320/A321 Airworthiness 
Limitations Section (hereafter referred to as `ALS') documents. The 
Damage Tolerant airworthiness limitation items are published in ALS 
Part 2, approved by EASA.
    The instructions contained in the ALS Part 2 have been 
identified as mandatory actions for continued airworthiness. Failure 
to comply with these instructions could result in an unsafe 
condition.
    Previously, EASA issued AD 2013-0147 (https://ad.easa.europa.eu/blob/easa_ad_2013_0147_superseded.pdf/AD_2013-0147_1) [which 
corresponds to FAA AD 2014-23-15, Amendment 39-18031 (80 FR 3871, 
January 26, 2015) to require accomplishment of all maintenance tasks 
as described in ALS Part 2 at Revision 02. The new ALS Part 2 
Revision 03 [Issue October 27, 2014] includes new and/or more 
restrictive items and was approved on 27 October 2014.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0147, which is superseded, and requires 
accomplishment of all maintenance tasks as described in ALS Part 2 
at Revision 03.

    The required action is revising the maintenance or inspection 
program to incorporate new or revised structural inspection 
requirements. The unsafe condition is fatigue cracking, accidental 
damage, or corrosion in principal structural elements, and WFD, which 
could result in reduced structural integrity of the airplane. You may 
examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6429.

Other Relevant Rulemaking

    We have issued NPRM Docket FAA-2015-6539, Directorate Identifier 
2015-NM-036-AD (80 FR 74723, November 30, 2015), for all Airbus Model 
A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 
airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-
111, -112, -211, -212, and -213 airplanes. That NPRM proposes to 
require repetitive inspections that reduce the compliance time for Task 
712111-01, Detailed Inspection of Forward Engine Mount Installation. 
Therefore, Task 712111-01 is not included in this proposed AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Part 2, Damage Tolerant Airworthiness Limitation 
Items (DT-ALI), Revision 04, dated December 18, 2015, of the A318/A319/
A320/A321 Airworthiness Limitation Section (ALS). The service 
information describes DT ALIs associated with WFD.
    Airbus has also issued Part 2, Damage Tolerant Airworthiness 
Limitation Items

[[Page 29200]]

(DT-ALI), Variation 4.2, dated January 15, 2016, of the A318/A319/A320/
A321 Airworthiness Limitation Section (ALS). The service information 
describes DT ALIs associated with WFD.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.
    This proposed AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections). Compliance with 
these actions is required by 14 CFR 91.403(c). For airplanes that have 
been previously modified, altered, or repaired in the areas addressed 
by this proposed AD, the operator might not be able to accomplish the 
actions described in the revisions. In this situation, to comply with 
14 CFR 91.403(c), the operator must request approval for an alternative 
method of compliance (AMOC) in accordance with the provisions of 
paragraph (k)(1) of this proposed AD. The request should include a 
description of changes to the required actions that will ensure the 
continued damage tolerance of the affected structure.

Differences Between This Proposed AD and the MCAI or Service 
Information

    This proposed AD differs from the MCAI in that it specifies 
revising the maintenance or inspection program, as applicable, to 
incorporate the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 
2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 
04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, 
Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 4.2, 
dated January 15, 2016. The MCAI specifies incorporating the ALIs 
specified in Airbus A318/A319/A320/A321 ALS Safe Life Airworthiness 
Limitation Section (ALS), Part 2, Damage Tolerant Airworthiness 
Limitation Items (DT-ALI), Revision 03, Issue October 27, 2014. We have 
coordinated this change with EASA.
    EASA has issued EASA Proposed Airworthiness Directive (PAD) 16-029, 
dated February 24, 2016, which specifies incorporating the ALI's in 
Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness 
Limitation Items (DT-ALI), Revision 04, dated December 18, 2015; and 
Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness 
Limitation Items (DT-ALI), Variation 4.2, dated January 15, 2016.
    The MCAI specifies that if there are findings from the ALS 
inspection tasks, corrective actions must be accomplished in accordance 
with Airbus maintenance documentation. However, this proposed AD does 
not include that requirement. Operators of U.S.-registered airplanes 
are required by general airworthiness and operational regulations to 
perform maintenance using methods that are acceptable to the FAA. We 
consider those methods to be adequate to address any corrective actions 
necessitated by the findings of ALS inspections required by this 
proposed AD.

Airworthiness Limitations Based on Type Design

    The FAA recently became aware of an issue related to the 
applicability of ADs that require incorporation of an ALS revision into 
an operator's maintenance or inspection program.
    Typically, when these types of ADs are issued by civil aviation 
authorities of other countries, they apply to all airplanes covered 
under an identified type certificate (TC). The corresponding FAA AD 
typically retains applicability to all of those airplanes. In addition, 
U.S. operators must operate their airplanes in an airworthy condition, 
in accordance with 14 CFR 91.7(a). Included in this obligation is the 
requirement to perform any maintenance or inspections specified in the 
ALS, and in accordance with the ALS as specified in 14 CFR 43.16 and 
91.403(c), unless an alternative has been approved by the FAA.
    When a type certificate is issued for a type design, the specific 
ALS, including revisions, is a part of that type design, as specified 
in 14 CFR 21.31(c). The sum effect of these operational and maintenance 
requirements is an obligation to comply with the ALS defined in the 
type design referenced in the manufacturer's conformity statement. This 
obligation may introduce a conflict with an AD that requires a specific 
ALS revision if new airplanes are delivered with a later revision as 
part of their type design.
    To address this conflict, the FAA has approved AMOCs that allow 
operators to incorporate the most recent ALS revision into their 
maintenance/inspection programs, in lieu of the ALS revision required 
by the AD. This eliminates the conflict and enables the operator to 
comply with both the AD and the type design.
    However, compliance with AMOCs is normally optional, and we 
recently became aware that some operators choose to retain the AD-
mandated ALS revision in their fleet-wide maintenance/inspection 
programs, including those for new airplanes delivered with later ALS 
revisions, to help standardize the maintenance of the fleet. To ensure 
that operators comply with the applicable ALS revision for newly 
delivered airplanes containing a later revision than that specified in 
an AD, we plan to limit the applicability of ADs that mandate ALS 
revisions to those airplanes that are subject to an earlier revision of 
the ALS, either as part of the type design or as mandated by an earlier 
AD.
    This proposed AD therefore applies to the airplanes identified in 
paragraph (c) of this proposed AD with an original certificate of 
airworthiness or original export certificate of airworthiness that was 
issued on or before the date of approval of the ALS revision identified 
in this proposed AD. Operators of airplanes with an original 
certificate of airworthiness or original export certificate of 
airworthiness issued after that date must comply with the airworthiness 
limitations specified as part of the approved type design and 
referenced on the type certificate data sheet.

Record of Ex Parte Communication

    In preparation of AD actions, it is the practice of the FAA to 
obtain technical information and information on the operational and 
economic impact from design approval holders and aircraft operators. We 
discussed certain issues related to this NPRM in a recent meeting with 
Airlines for America (A4A). Shortly after this NPRM is published, we 
will post a summary of this meeting in the rulemaking docket. For 
information on locating the docket, see ``Examining the AD Docket.''

Costs of Compliance

    We estimate that this proposed AD affects 959 airplanes of U.S. 
registry.
    The actions required by AD 2015-05-02, and retained in this 
proposed AD take about 2 work-hours per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are

[[Page 29201]]

required by AD 2015-05-02 is $170 per product.
    We also estimate that it would take about 2 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $163,030, or $170 
per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015), and 
adding the following new AD:

Airbus: Docket No. FAA-2016-6429; Directorate Identifier 2015-NM-
117-AD.

(a) Comments Due Date

    We must receive comments by June 27, 2016.

(b) Affected ADs

    This AD replaces AD 2015-05-02, Amendment 39-18112 (80 FR 15152, 
March 23, 2015) (``AD 2015-05-02'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, with 
an original certificate of airworthiness or original export 
certificate of airworthiness issued on or before January 15, 2016.
    (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 05, Periodic 
Inspections.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) which indicates that principal structural elements and 
certain life limited parts are subject to widespread fatigue damage 
(WFD). We are issuing this AD to prevent fatigue cracking, 
accidental damage, or corrosion in principal structural elements, 
and WFD, which could result in reduced structural integrity of the 
airplane.

(f) Compliance

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

(g) Retained Maintenance or Inspection Program Revision, With No 
Changes

    This paragraph restates the requirements of paragraph (n) of AD 
2015-05-02, with no changes. Within 30 days after March 2, 2015 (the 
effective date of AD 2014-23-15, Amendment 39-18031 (80 FR 3871, 
January 26, 2015) (``AD 2014-23-15'')), revise the maintenance or 
inspection program, as applicable, to incorporate the Airworthiness 
Limitation Items (ALIs) specified in paragraphs (g)(1) and (g)(2) of 
this AD. The initial compliance time for accomplishing the actions 
is at the applicable time identified in the ALIs specified in 
paragraphs (g)(1) and (g)(2) of this AD; or within 4 months after 
March 2, 2015 (the effective date of AD 2014-23-15); whichever 
occurs later.
    (1) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
    (2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant 
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 
2013.

(h) Retained Limitation: No Alternative Actions, Intervals, and/or 
Critical Design Configuration Control Limitations (CDCCLs), With 
Exception

    This paragraph restates the requirements of paragraph (o) of AD 
2015-05-02, with an exception. Except as required by paragraph (i) 
of this AD, after accomplishing the revision required by paragraph 
(g) of this AD, no alternative actions (e.g., inspections), 
intervals, and/or CDCCLs may be used unless the actions, intervals, 
and/or CDCCLs are approved as an alternative method of compliance 
(AMOC) in accordance with the procedures specified in paragraph 
(k)(1) of this AD.

(i) New Requirement of This AD: Maintenance or Inspection Program 
Revision

    Within 60 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2, Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Revision 04, dated 
December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Variation 4.2, 
dated January 15, 2016. The initial compliance time for 
accomplishing the actions is at the applicable time identified in 
the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2, Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Revision 04, dated 
December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Variation 4.2, 
dated January 15, 2016; without exceeding the inspection intervals 
in the ALIs specified in the service information identified in 
paragraph (g)(2) of this AD, except for the ALI tasks identified in 
paragraphs (i)(1) though (i)(4) of this AD. Accomplishing these 
actions terminates the requirements of paragraph (g)(2) of this AD.
    (1) Task 712111-01-1, ``Detailed Inspection of Forward Engine 
Mount Installation.''
    (2) Task 712111-01-2, ``Detailed Inspection of Forward Engine 
Mount Installation.''
    (3) Task 712111-01-3, ``Detailed Inspection of Forward Engine 
Mount Installation.''
    (4) Task 712111-01-4, ``Detailed Inspection of Forward Engine 
Mount Installation.''

[[Page 29202]]

(j) New No Alternative Actions and/or Intervals

    After accomplishing the revision required by paragraph (i) of 
this AD, no alternative actions (e.g., inspections) and/or intervals 
may be used unless the actions and/or intervals are approved as an 
AMOC in accordance with the procedures specified in paragraph (k)(1) 
of this AD.

(k) 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 for AD 2015-05-02, are approved 
as AMOCs for the corresponding provisions of paragraphs (g) and (h) 
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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0083, dated May 12, 2015, 
for related information. This MCAI may be found in the AD docket on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-6429.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on May 3, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10914 Filed 5-10-16; 8:45 am]
 BILLING CODE 4910-13-P
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