83 FR 5579 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 27 (February 8, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 27 (February 8, 2018)
| Page Range | 5579-5584 | |
| FR Document | 2018-02084 |
[Federal Register Volume 83, Number 27 (Thursday, February 8, 2018)] [Proposed Rules] [Pages 5579-5584] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-02084] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0071; Product Identifier 2017-NM-063-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) 2016-23- 01, which applies to all Airbus Model A310 series airplanes. AD 2016- 23-01 requires repetitive detailed inspections for cracking around the fastener holes in certain areas of the wing top skin panels, supplemental repetitive ultrasonic inspections for cracking around the fastener holes in certain other areas of the wing top skin panels, and repair if necessary. Since we issued AD 2016-23-01, an evaluation done by the design approval holder (DAH) indicates that the wing top skin panel attachment holes at a certain area are also subject to widespread fatigue damage (WFD). This proposed AD would add an inspection and modification of the attachment holes of the wing top skin panels at a certain area. This proposed AD also includes terminating action for certain inspections. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by March 26, 2018. 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 http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. Hand Delivery: 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 Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425- 227-1221. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0071; 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: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425- 227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0071; Product Identifier 2017-NM-063-AD'' at the beginning of [[Page 5580]] your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2016-23-01, Amendment 39-18708 (81 FR 78899, November 10, 2016) (``AD 2016-23-01''), for all Airbus Model A310 series airplanes. AD 2016-23-01 was prompted by development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. AD 2016-23-01 requires repetitive detailed inspections for cracking around the fastener holes in certain wing top skin panels between the front and rear spars on the left- and right-hand sides of the fuselage, supplemental repetitive ultrasonic inspections for cracking around the fastener holes in wing top skin panels 1 and 2 at ribs 2 and 3, and repair if necessary. We issued AD 2016-23-01 to detect and correct fatigue cracking around the fastener holes, which could result in reduced structural integrity of the airplane. Since we issued AD 2016-23-01, WFD analysis identified structural modification points for certain fastener holes located at each attachment from stringer (STG) 2 through STG10 at ribs 2 and 3 on both wings. Inspections and modifications were developed to reset the fatigue life of the attachment holes at the top skin attachment to rib 2 and rib 3 up to the limit of validity (LOV). Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread 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. This condition is known as WFD. It is associated with general degradation of large areas of structure with similar structural details and stress levels. 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 an 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. Actions Since AD 2016-23-01 Was Issued Since we issued AD 2016-23-01, we have received a report that an evaluation done by the DAH indicates that the wing top skin panel attachment holes at ribs 2 and 3 are also subject to WFD, and an analysis identified structural modification points for certain fastener holes located at each attachment from STG2 through STG10 at ribs 2 and 3 on both wings. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0081, dated May 8, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A310 series airplanes. The MCAI states: Following scheduled maintenance, cracks were found around the wing top skin panels fastener holes at Rib 2, between Stringer (STG) 2 and STG14. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. To address this issue, Airbus developed an inspection programme, and published Service Bulletin (SB) A310-57-2096, providing instructions for repetitive detailed inspections (DET) to ensure that any visible cracks in the wing top skin panels 1 and 2 along Rib 2 are detected on time and repaired appropriately. Consequently, EASA issued AD 2008-0211 [which corresponds to FAA AD 2010-04-03] to require implementation of that inspection programme. After that [EASA] AD was issued, Airbus improved the inspection programme, revising SB A310-57-2096 accordingly, to include a special detailed inspection (SDI), using an ultrasonic method, to allow earlier crack detection, to subsequently reduce the scope of potential repair action, and to extend the intervals of the repetitive inspections. Consequently, EASA issued AD 2014-0200 (later revised), retaining the requirements of EASA AD 2008-0211, which was superseded, and required supplementary repetitive SDI [for cracking] of the wing top skin panel 1 and 2 between STG2 and STG10 at Rib 2 [and repair if needed], as described in Airbus SB A310-57-2096 Revision 02. Since EASA AD 2014-0200R1 was issued, a Widespread Fatigue Damage (WFD) analysis concluded that the inspection programme had to be extended to include the wing top skin panels at Rib 3 attachments, and Airbus issued SB A310-57-2096 Revision 03 accordingly, to provide the necessary instructions. Consequently, EASA issued [EASA] AD 2016-0005 [which corresponds to FAA AD 2016- 23-01], retaining the requirements of EASA AD 2014-0200R1, which was superseded, and extending the inspection area to include Rib 3. In addition to changes to the inspected area, WFD analysis identified structural modification points for certain fastener holes, located at each attachment from STG2 to STG10, at Ribs 2 and 3 on both wings. Airbus developed modification (mod) 13785 and mod 13786, consisting of an SDI, followed by an oversize of the defined holes on Ribs 2 and 3 on both wings. Airbus issued SB A310-57-2106 and SB A310-57-2107 to provide in-service modification instructions for top skin attachments to Rib 2 and Rib 3 respectively. Accomplishment of these modifications at the specified time will reset the fatigue life of the attachment holes at the top skin attachment to Rib 2 and Rib 3 to the Limit of Validity (LOV). Airbus issued inspection SB A310-57-2096 Revision 04 to account for the inspection requirements post-modification. For the reasons describe above, this [EASA] AD retains the requirements of EASA AD 2016-0005, which is superseded, requires modifications to the top skin attachment holes at Rib 2 and Rib 3, and [[Page 5581]] defines the inspection requirements for Rib 2 and Rib 3 after modification. Modification of the fastener holes at top skin ribs 2 and 3 constitutes terminating action for certain repetitive special detailed inspections. You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0071. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A310-57-2096, Revision 04, dated December 5, 2016. This service information describes procedures for detailed and ultrasonic inspections for cracking around the fastener holes of wing top skin panels 1 and 2, at ribs 2 and 3, on the left- and right-hand sides of the fuselage. Airbus Service Bulletin A310-57-2106, dated November 14, 2016. This service information describes procedures for a special detailed inspection and modification of the fastener holes of wing top skin panels 1 and 2, at rib 2. Airbus Service Bulletin A310-57-2107, dated November 14, 2016. This service information describes procedures for a special detailed inspection and modification of the fastener holes of wing top skin panels 1 and 2, at rib 3. 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 the same type design. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 8 airplanes of U.S. registry. The actions required by AD 2016-23-01, and retained in this proposed AD, take about 8 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 required by AD 2016-23-01 on U.S. operators to be $5,440, or $680 per product. We also estimate that it would take about 95 work-hours per product to comply with the basic requirements of this proposed AD. Required parts would cost about $10,200 per product. 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 $146,200, or $18,275 per product. In addition, we estimate that any necessary modification would take about 40 work-hours and require parts costing $10,000, for a cost of $13,400 per product. We have no way of determining the number of aircraft that might need these actions. 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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) 2016-23-01, Amendment 39-18708 (81 FR 78899, November 10, 2016), and adding the following new AD: Airbus: Docket No. FAA-2018-0071; Product Identifier 2017-NM-063-AD. (a) Comments Due Date We must receive comments by March 26, 2018. (b) Affected ADs This AD replaces AD 2016-23-01, Amendment 39-18708 (81 FR 78899, November 10, 2016) (``AD 2016-23-01''). [[Page 5582]] (c) Applicability This AD applies to all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by an evaluation done by the design approval holder (DAH) indicating that the wing top skin panel attachment holes at ribs 2 and 3 are also subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking around the fastener holes, 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 Repetitive Inspections, With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2016-23-01, with revised service information. Except as required by paragraph (i) of this AD: Within the initial compliance time and thereafter at the repetitive intervals specified in paragraphs (h)(1) through (h)(3) of this AD, as applicable, accomplish the actions specified in paragraphs (g)(1) and (g)(2) of this AD concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015, or Revision 04, dated December 5, 2016; except as provided by paragraph (j) of this AD. As of the effective date of this AD, use only Airbus Service Bulletin A310-57-2096, Revision 04, dated December 5, 2016, to accomplish the required actions. (1) Accomplish a detailed inspection for cracking around the fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 3, between the front and rear spars on the left- and right-hand sides of the fuselage. (2) Accomplish an ultrasonic inspection for cracking around the fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 3, between stringer (STG) 2 and STG10 on the left- and right-hand sides of the fuselage. (h) Retained Compliance Times for Airplanes Not Previously Inspected, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2016-23-01, with no changes. (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at intervals not to exceed 2,000 flight cycles or 4,100 flight hours, whichever occurs first. (i) Prior to the accumulation of 18,700 flight cycles or 37,400 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after December 15, 2016 (the effective date of AD 2016-23-01). (2) For Model A310-304, -322, -324, and -325 airplanes having an average flight time (AFT) of less than 4 hours: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at intervals not to exceed 2,000 flight cycles or 5,600 flight hours, whichever occurs first. (i) Prior to the accumulation of 17,300 flight cycles or 48,400 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after December 15, 2016 (the effective date of AD 2016-23-01). (3) For Model A310-304, -322, -324, and -325 airplanes having an AFT of equal to or more than 4 hours: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at intervals not to exceed 1,500 flight cycles or 7,500 flight hours, whichever occurs first. (i) Prior to the accumulation of 12,800 flight cycles or 64,300 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after December 15, 2016 (the effective date of AD 2016-23-01). (i) Retained Compliance Times for Airplanes Previously Inspected, With Revised Service Information This paragraph restates the requirements of paragraph (i) of AD 2016-23-01, with revised service information. For airplanes previously inspected before December 15, 2016 (the effective date of AD 2016-23-01), using Airbus Service Bulletin A310-57-2096, dated May 6, 2008; Airbus Service Bulletin A310-57- 2096, Revision 01, dated August 5, 2010; or Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014: At the applicable compliance times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, accomplish the actions specified in paragraphs (g)(1) and (g)(2) concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015, or Revision 04, dated December 5, 2016. As of the effective date of this AD, use only Airbus Service Bulletin A310-57-2096, Revision 04, dated December 5, 2016, to accomplish the required actions. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the repetitive intervals specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable. (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD within 3,500 flight hours or 1,700 flight cycles, whichever occurs first since the most recent inspection. (2) For Model A310-304, -322, -324, and -325 airplanes having an AFT of less than 4 hours: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD within 4,600 flight hours or 1,600 flight cycles, whichever occurs first since the most recent inspection. (3) For Model A310-304, -322, -324, and -325 airplanes having an AFT of equal to or more than 4 hours: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD within 6,100 flight hours or 1,200 flight cycles, whichever occurs first since the most recent inspection. (j) Retained Compliance Times if No Ultrasonic Equipment Is Available, With Revised Service Information This paragraph restates the requirements of paragraph (j) of AD 2016-23-01, with revised service information. If no ultrasonic equipment is available for the initial or second inspection required by paragraph (g) or (h) of this AD, accomplish the detailed inspection specified in paragraph (g)(1) of this AD within the applicable compliance times specified in paragraphs (j)(1) and (j)(2) of this AD. After accomplishing the detailed inspection, do the inspections specified in paragraphs (g)(1) and (g)(2) of this AD at the applicable compliance times specified by paragraphs (i)(1), (i)(2), and (i)(3) of this AD. Subsequently, repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable repetitive intervals specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) For airplanes not previously inspected before December 15, 2016 (the effective date of AD 2016-23-01), using the service information identified in paragraph (j)(2)(i), (j)(2)(ii), (j)(2)(iii), or (j)(2)(iv) of this AD: Do the actions required by paragraph (g)(1) of this AD within the initial compliance time specified by paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable. (2) For airplanes previously inspected before December 15, 2016 (the effective date of AD 2016-23-01), using the service information identified in paragraph (j)(2)(i), (j)(2)(ii), (j)(2)(iii), or (j)(2)(iv) of this AD: Do the actions required by paragraph (g)(1) of this AD within the applicable compliance times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (i) Airbus Service Bulletin A310-57-2096, dated May 6, 2008. (ii) Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010. (iii) Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014. (iv) Airbus Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015. (k) Retained Repair of Cracking, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2016-23-01, with no changes. If any cracking is found during any inspection required by paragraph (g), (h), (i), or (j) of this AD, before further flight, repair the cracking using a method approved by the Manager, International Section, Transport Standards Branch, 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. Accomplishing the repair specified in this paragraph terminates the repetitive inspections required by paragraph (g), (h), (i), or (j) of this AD, as applicable, for the repaired area only. [[Page 5583]] (l) Retained Definition of AFT, With No Changes This paragraph restates the requirements of paragraph (l) of AD 2016-23-01, with no changes. For the purposes of this AD, the AFT should be established as specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD for the determination of the compliance times. (1) The inspection threshold is defined as the total flight hours accumulated (counted from take-off to touch-down), divided by the total number of flight cycles accumulated at the effective date of this AD. (2) The initial inspection interval is defined as the total flight hours accumulated divided by the total number of flight cycles accumulated at the time of the initial inspection threshold. (3) The second inspection interval is defined as the total flight hours accumulated divided by the total number of flight cycles accumulated between the initial and second inspection threshold. For all inspection intervals onwards, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections. (m) New Requirements of This AD: Rib 2 Inspection and Modification At the compliance time specified in paragraph (n) of this AD, as applicable, accomplish the actions specified in paragraphs (m)(1) and (m)(2) of this AD concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2106, dated November 14, 2016. (1) Accomplish a special detailed inspection to determine the diameter of the fastener holes in the wing top skin panels 1 and 2, at rib 2 of both wings. (2) Modify the fastener holes. (n) New Compliance Times for Rib 2 Inspection and Modification (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraphs (m)(1) and (m)(2) of this AD at the later of the times specified in paragraphs (n)(1)(i) and (n)(1)(ii) of this AD. (i) Prior to the accumulation of 40,000 flight cycles or 93,300 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (2) For Model A310-304, -322, -324, and -325 airplanes having an average flight time (AFT) of less than 4 hours: Do the actions required by paragraphs (m)(1) and (m)(2) of this AD at the later of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. (i) Prior to the accumulation of 40,000 flight cycles or 116,000 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (3) For Model A310-304, -322, -324, and -325 airplanes having an AFT of 4 hours or more: Do the actions required by paragraphs (m)(1) and (m)(2) of this AD at the later of the times specified in paragraphs (n)(3)(i) and (n)(3)(ii) of this AD. (i) Prior to the accumulation of 30,000 flight cycles or 150,000 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (o) New Requirements of This AD: Rib 3 Inspection and Modification At the compliance time specified in paragraph (p) of this AD, as applicable, accomplish the actions specified in paragraphs (o)(1) and (o)(2) of this AD concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2107, dated November 14, 2016. (1) Accomplish a special detailed inspection to determine the diameter of the fastener holes in the wing top skin panels 1 and 2, at rib 3 of both wings. (2) Modify the fastener holes. (p) New Compliance Times for Rib 3 Inspection and Modification (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraphs (o)(1) and (o)(2) of this AD at the later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this AD. (i) Prior to the accumulation of 46,400 flight cycles or 92,900 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (2) For Model A310-304, -322, -324, and -325 airplanes having an average flight time (AFT) of less than 4 hours: Do the actions required by paragraphs (o)(1) and (o)(2) of this AD at the later of the times specified in paragraphs (p)(2)(i) and (p)(2)(ii) of this AD. (i) Prior to the accumulation of 45,400 flight cycles or 127,300 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (3) For Model A310-304, -322, -324, and -325 airplanes having an AFT of 4 hours or more: Do the actions required by paragraphs (o)(1) and (o)(2) of this AD at the later of the times specified in paragraphs (p)(3)(i) and (p)(3)(ii) of this AD. (i) Prior to the accumulation of 33,800 flight cycles or 169,000 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (q) New Corrective Actions If any cracking is found during any inspection required by paragraph (m), (n), (o), or (p) of this AD, before further flight, repair the cracking using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. Accomplishing the repair specified in this paragraph terminates the repetitive inspections required by paragraph (g), (h), (i), or (j) of this AD, as applicable, for the repaired area only. (r) New Terminating Actions (1) Accomplishment of the modification specified in paragraph (m) of this AD constitutes terminating action for the repetitive special detailed inspections required by paragraph (g)(2) of this AD for the modified fastener holes at top skin rib 2 for that airplane. After modification, the un-modified fastener holes at top skin rib 2 between the front and rear spars remain subject to the repetitive inspections required by paragraph (g)(1) of this AD. (2) Accomplishment of the modification specified in paragraph (o) of this AD constitutes terminating action for the repetitive special detailed inspections required by paragraph (g)(2) of this AD for the modified fastener holes at top skin rib 3 for that airplane. After modification, the un-modified fastener holes at top skin rib 3 between the front and rear spars remain subject to the repetitive inspection required by paragraph (g)(1) of this AD. (s) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 the attention of the person identified in paragraph (t)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0081, dated May 8, 2017, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0071. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, [[Page 5584]] International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425- 227-1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; internet: http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 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 January 25, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-02084 Filed 2-7-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 27 / Thursday, February 8, 2018 / Proposed Rules 5579
specification wire types identified above; and Engineer, Propulsion Section, FAA, Seattle DATES: We must receive comments on
NEMA WC 27500 cables that are constructed ACO Branch, 1601 Lind Avenue SW, Renton, this proposed AD by March 26, 2018.
from the SAE specification wire types WA 98057–3356; phone: 425–917–6498; fax:
ADDRESSES: You may send comments,
identified above. 425–917–6590; email: christopher.r.baker@
(2) Where AWL No. 28–AWL–03 identifies faa.gov. using the procedures found in 14 CFR
TFE–2X Standard wall for wire sleeving, the (2) For service information identified in 11.43 and 11.45, by any of the following
following acceptable sleeving materials can this AD, contact Boeing Commercial methods:
be added to AWL No. 28–AWL–03: Roundit Airplanes, Attention: Contractual & Data • Federal eRulemaking Portal: Go to
2000NX and Varglas Type HO, HP, or HM, Services (C&DS), 2600 Westminster Blvd., http://www.regulations.gov. Follow the
Grade A. MC 110–SK57, Seal Beach, CA 90740–5600; instructions for submitting comments.
(i) No Alternative Actions, Intervals, and
telephone 562–797–1717; internet https:// • Fax: 202–493–2251.
www.myboeingfleet.com. You may view this • Mail: U.S. Department of
Critical Design Configuration Control
service information at the FAA, Transport
Limitations (CDCCLs) Transportation, Docket Operations, M–
Standards Branch, 1601 Lind Avenue SW,
After the maintenance or inspection Renton, WA. For information on the 30, West Building Ground Floor, Room
program, as applicable, has been revised as availability of this material at the FAA, call W12–140, 1200 New Jersey Avenue SE,
required by paragraph (g) of this AD, no 425–227–1221. Washington, DC 20590.
alternative actions (e.g., inspections), • Hand Delivery: Deliver to Mail
intervals, and CDCCLs may be used unless Issued in Renton, Washington, on January
26, 2018. address above between 9 a.m. and 5
the actions, intervals, and CDCCLs are p.m., Monday through Friday, except
approved as an alternative method of Michael Kaszycki,
compliance (AMOC), in accordance with the
Federal holidays.
Acting Director, System Oversight Division,
procedures specified in paragraph (k) of this For service information identified in
Aircraft Certification Service.
AD. this NPRM, contact Airbus SAS,
[FR Doc. 2018–02085 Filed 2–7–18; 8:45 am]
Airworthiness Office—EAW, 1 Rond
(j) Terminating Actions BILLING CODE 4910–13–P Point Maurice Bellonte, 31707 Blagnac
Accomplishment of the revision required Cedex, France; telephone: +33 5 61 93
by paragraph (g) of this AD terminates the 36 96; fax: +33 5 61 93 44 51; email:
actions specified in paragraphs (j)(1) through DEPARTMENT OF TRANSPORTATION account.airworth-eas@airbus.com;
(j)(5) of this AD for the airplane on which the
revision has been incorporated. Federal Aviation Administration internet: http://www.airbus.com. You
(1) The revision required by paragraph (g) may view this referenced service
of AD 2008–04–10 R1. 14 CFR Part 39 information at the FAA, Transport
(2) The revision required by paragraph (h) Standards Branch, 1601 Lind Avenue
of AD 2009–05–03. [Docket No. FAA–2018–0071; Product SW, Renton, WA. For information on
(3) The revision required by paragraph (j) Identifier 2017–NM–063–AD] the availability of this material at the
of AD 2011–12–05. FAA, call 425–227–1221.
(4) The revision required by paragraph (h) RIN 2120–AA64
of AD 2013–22–03. Examining the AD Docket
(5) The revision required by paragraphs Airworthiness Directives; Airbus
(n)(1) and (n)(2) of AD 2013–24–15. You may examine the AD docket on
Airplanes the internet at http://
(k) Alternative Methods of Compliance www.regulations.gov by searching for
(AMOCs) AGENCY: Federal Aviation
Administration (FAA), DOT. and locating Docket No. FAA–2018–
(1) The Manager, Seattle ACO Branch, 0071; or in person at the Docket
FAA, has the authority to approve AMOCs ACTION: Notice of proposed rulemaking
Management Facility between 9 a.m.
for this AD, if requested using the procedures (NPRM).
and 5 p.m., Monday through Friday,
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your SUMMARY: We propose to supersede except Federal holidays. The AD docket
principal inspector or local Flight Standards Airworthiness Directive (AD) 2016–23– contains this proposed AD, the
District Office, as appropriate. If sending 01, which applies to all Airbus Model regulatory evaluation, any comments
information directly to the manager of the A310 series airplanes. AD 2016–23–01 received, and other information. The
certification office, send it to the attention of requires repetitive detailed inspections street address for the Docket Operations
the person identified in paragraph (l)(1) of for cracking around the fastener holes in office (telephone: 800–647–5527) is in
this AD. Information may be emailed to: 9- the ADDRESSES section. Comments will
ANM-Seattle-ACO-AMOC-Requests@faa.gov. certain areas of the wing top skin
panels, supplemental repetitive be available in the AD docket shortly
(2) Before using any approved AMOC,
notify your appropriate principal inspector, ultrasonic inspections for cracking after receipt.
or lacking a principal inspector, the manager around the fastener holes in certain FOR FURTHER INFORMATION CONTACT: Dan
of the local flight standards district office/ other areas of the wing top skin panels, Rodina, Aerospace Engineer,
certificate holding district office. and repair if necessary. Since we issued International Section, Transport
(3) An AMOC that provides an acceptable AD 2016–23–01, an evaluation done by Standards Branch, FAA, 1601 Lind
level of safety may be used for any repair, the design approval holder (DAH) Avenue SW, Renton, WA 98057–3356;
modification, or alteration required by this
AD if it is approved by the Boeing indicates that the wing top skin panel telephone: 425–227–2125; fax: 425–
Commercial Airplanes Organization attachment holes at a certain area are 227–1149.
Designation Authorization (ODA) that has also subject to widespread fatigue SUPPLEMENTARY INFORMATION:
been authorized by the Manager, Seattle ACO damage (WFD). This proposed AD
daltland on DSKBBV9HB2PROD with PROPOSALS
Branch, to make those findings. To be would add an inspection and Comments Invited
approved, the repair method, modification modification of the attachment holes of We invite you to send any written
deviation, or alteration deviation must meet the wing top skin panels at a certain relevant data, views, or arguments about
the certification basis of the airplane, and the area. This proposed AD also includes this proposed AD. Send your comments
approval must specifically refer to this AD.
terminating action for certain to an address listed under the
(l) Related Information inspections. We are proposing this AD ADDRESSES section. Include ‘‘Docket No.
(1) For more information about this AD, to address the unsafe condition on these FAA–2018–0071; Product Identifier
contact Christopher Baker, Aerospace products. 2017–NM–063–AD’’ at the beginning of
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![5580 Federal Register / Vol. 83, No. 27 / Thursday, February 8, 2018 / Proposed Rules
your comments. We specifically invite structural details and stress levels. As for all Airbus Model A310 series
comments on the overall regulatory, an airplane ages, WFD will likely occur, airplanes. The MCAI states:
economic, environmental, and energy and will certainly occur if the airplane Following scheduled maintenance, cracks
aspects of this proposed AD. We will is operated long enough without any were found around the wing top skin panels
consider all comments received by the intervention. fastener holes at Rib 2, between Stringer
closing date and may amend this The FAA’s WFD final rule (75 FR (STG) 2 and STG14.
proposed AD based on those comments. 69746, November 15, 2010) became This condition, if not detected and
We will post all comments we effective on January 14, 2011. The WFD corrected, could reduce the structural
receive, without change, to http:// rule requires certain actions to prevent integrity of the aeroplane.
www.regulations.gov, including any structural failure due to WFD To address this issue, Airbus developed an
personal information you provide. We throughout the operational life of inspection programme, and published
will also post a report summarizing each certain existing transport category Service Bulletin (SB) A310–57–2096,
providing instructions for repetitive detailed
substantive verbal contact we receive airplanes and all of these airplanes that
inspections (DET) to ensure that any visible
about this proposed AD. will be certificated in the future. For cracks in the wing top skin panels 1 and 2
existing and future airplanes subject to along Rib 2 are detected on time and repaired
Discussion
the WFD rule, the rule requires that appropriately. Consequently, EASA issued
We issued AD 2016–23–01, DAHs establish an LOV of the AD 2008–0211 [which corresponds to FAA
Amendment 39–18708 (81 FR 78899, engineering data that support the AD 2010–04–03] to require implementation
November 10, 2016) (‘‘AD 2016–23– structural maintenance program. of that inspection programme.
01’’), for all Airbus Model A310 series Operators affected by the WFD rule may After that [EASA] AD was issued, Airbus
airplanes. AD 2016–23–01 was not fly an airplane beyond its LOV, improved the inspection programme, revising
prompted by development of an unless an extended LOV is approved. SB A310–57–2096 accordingly, to include a
ultrasonic inspection program to allow The WFD rule (75 FR 69746, special detailed inspection (SDI), using an
for earlier crack detection and extended ultrasonic method, to allow earlier crack
November 15, 2010) does not require
detection, to subsequently reduce the scope
repetitive inspection intervals. AD identifying and developing maintenance of potential repair action, and to extend the
2016–23–01 requires repetitive detailed actions if the DAHs can show that such intervals of the repetitive inspections.
inspections for cracking around the actions are not necessary to prevent Consequently, EASA issued AD 2014–0200
fastener holes in certain wing top skin WFD before the airplane reaches the (later revised), retaining the requirements of
panels between the front and rear spars LOV. Many LOVs, however, do depend EASA AD 2008–0211, which was
on the left- and right-hand sides of the on accomplishment of future superseded, and required supplementary
fuselage, supplemental repetitive maintenance actions. As stated in the repetitive SDI [for cracking] of the wing top
ultrasonic inspections for cracking WFD rule, any maintenance actions skin panel 1 and 2 between STG2 and STG10
around the fastener holes in wing top necessary to reach the LOV will be at Rib 2 [and repair if needed], as described
skin panels 1 and 2 at ribs 2 and 3, and in Airbus SB A310–57–2096 Revision 02.
mandated by airworthiness directives Since EASA AD 2014–0200R1 was issued,
repair if necessary. We issued AD 2016– through separate rulemaking actions. a Widespread Fatigue Damage (WFD)
23–01 to detect and correct fatigue In the context of WFD, this action is analysis concluded that the inspection
cracking around the fastener holes, necessary to enable DAHs to propose programme had to be extended to include the
which could result in reduced structural LOVs that allow operators the longest wing top skin panels at Rib 3 attachments,
integrity of the airplane. operational lives for their airplanes, and and Airbus issued SB A310–57–2096
Since we issued AD 2016–23–01, still ensure that WFD will not occur. Revision 03 accordingly, to provide the
WFD analysis identified structural This approach allows for an necessary instructions. Consequently, EASA
modification points for certain fastener implementation strategy that provides issued [EASA] AD 2016–0005 [which
holes located at each attachment from flexibility to DAHs in determining the corresponds to FAA AD 2016–23–01],
stringer (STG) 2 through STG10 at ribs retaining the requirements of EASA AD
timing of service information 2014–0200R1, which was superseded, and
2 and 3 on both wings. Inspections and development (with FAA approval), extending the inspection area to include
modifications were developed to reset while providing operators with certainty Rib 3.
the fatigue life of the attachment holes regarding the LOV applicable to their In addition to changes to the inspected
at the top skin attachment to rib 2 and airplanes. area, WFD analysis identified structural
rib 3 up to the limit of validity (LOV). modification points for certain fastener holes,
Fatigue damage can occur locally, in Actions Since AD 2016–23–01 Was located at each attachment from STG2 to
small areas or structural design details, Issued STG10, at Ribs 2 and 3 on both wings.
or globally, in widespread areas. Since we issued AD 2016–23–01, we Airbus developed modification (mod)
Multiple-site damage is widespread have received a report that an 13785 and mod 13786, consisting of an SDI,
damage that occurs in a large structural evaluation done by the DAH indicates followed by an oversize of the defined holes
on Ribs 2 and 3 on both wings. Airbus issued
element such as a single rivet line of a that the wing top skin panel attachment SB A310–57–2106 and SB A310–57–2107 to
lap splice joining two large skin panels. holes at ribs 2 and 3 are also subject to provide in-service modification instructions
Widespread damage can also occur in WFD, and an analysis identified for top skin attachments to Rib 2 and Rib 3
multiple elements such as adjacent structural modification points for respectively. Accomplishment of these
frames or stringers. Multiple-site certain fastener holes located at each modifications at the specified time will reset
damage and multiple-element damage attachment from STG2 through STG10 the fatigue life of the attachment holes at the
cracks are typically too small initially to at ribs 2 and 3 on both wings. top skin attachment to Rib 2 and Rib 3 to the
daltland on DSKBBV9HB2PROD with PROPOSALS
be reliably detected with normal The European Aviation Safety Agency Limit of Validity (LOV). Airbus issued
inspection methods. Without (EASA), which is the Technical Agent inspection SB A310–57–2096 Revision 04 to
for the Member States of the European account for the inspection requirements post-
intervention, these cracks will grow,
modification.
and eventually compromise the Union, has issued EASA AD 2017–0081, For the reasons describe above, this
structural integrity of the airplane. This dated May 8, 2017 (referred to after this [EASA] AD retains the requirements of EASA
condition is known as WFD. It is as the Mandatory Continuing AD 2016–0005, which is superseded,
associated with general degradation of Airworthiness Information, or ‘‘the requires modifications to the top skin
large areas of structure with similar MCAI’’), to correct an unsafe condition attachment holes at Rib 2 and Rib 3, and
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![Federal Register / Vol. 83, No. 27 / Thursday, February 8, 2018 / Proposed Rules 5581
defines the inspection requirements for Rib 2 WFD before it becomes a hazard to and Airworthiness Division, but during
and Rib 3 after modification. flight. We will not grant any extensions this transition period, the Executive
Modification of the fastener holes at of the compliance time to complete any Director has delegated the authority to
top skin ribs 2 and 3 constitutes AD-mandated service bulletin related to issue ADs applicable to transport
terminating action for certain repetitive WFD without extensive new data that category airplanes to the Director of the
special detailed inspections. You may would substantiate and clearly warrant System Oversight Division.
examine the MCAI in the AD docket on such an extension.
Regulatory Findings
the internet at http:// Costs of Compliance
www.regulations.gov by searching for We determined that this proposed AD
and locating Docket No. FAA–2018– We estimate that this proposed AD would not have federalism implications
0071. affects 8 airplanes of U.S. registry. under Executive Order 13132. This
The actions required by AD 2016–23– proposed AD would not have a
Related Service Information Under 1 01, and retained in this proposed AD, substantial direct effect on the States, on
CFR Part 51 take about 8 work-hours per product, at the relationship between the national
Airbus has issued the following an average labor rate of $85 per work- Government and the States, or on the
service information. hour. Based on these figures, the distribution of power and
• Airbus Service Bulletin A310–57– estimated cost of the actions that are responsibilities among the various
2096, Revision 04, dated December 5, required by AD 2016–23–01 on U.S. levels of government.
2016. This service information describes operators to be $5,440, or $680 per
For the reasons discussed above, I
procedures for detailed and ultrasonic product.
We also estimate that it would take certify this proposed regulation:
inspections for cracking around the
fastener holes of wing top skin panels 1 about 95 work-hours per product to 1. Is not a ‘‘significant regulatory
and 2, at ribs 2 and 3, on the left- and comply with the basic requirements of action’’ under Executive Order 12866;
right-hand sides of the fuselage. this proposed AD. Required parts would 2. Is not a ‘‘significant rule’’ under the
• Airbus Service Bulletin A310–57– cost about $10,200 per product. The DOT Regulatory Policies and Procedures
2106, dated November 14, 2016. This average labor rate is $85 per work-hour. (44 FR 11034, February 26, 1979);
service information describes Based on these figures, we estimate the 3. Will not affect intrastate aviation in
procedures for a special detailed cost of this proposed AD on U.S. Alaska; and
inspection and modification of the operators to be $146,200, or $18,275 per 4. Will not have a significant
fastener holes of wing top skin panels 1 product. economic impact, positive or negative,
and 2, at rib 2. In addition, we estimate that any on a substantial number of small entities
• Airbus Service Bulletin A310–57– necessary modification would take under the criteria of the Regulatory
2107, dated November 14, 2016. This about 40 work-hours and require parts Flexibility Act.
service information describes costing $10,000, for a cost of $13,400
procedures for a special detailed per product. We have no way of List of Subjects in 14 CFR Part 39
inspection and modification of the determining the number of aircraft that Air transportation, Aircraft, Aviation
fastener holes of wing top skin panels 1 might need these actions. safety, Incorporation by reference,
and 2, at rib 3. Authority for This Rulemaking Safety.
This service information is reasonably
available because the interested parties Title 49 of the United States Code The Proposed Amendment
have access to it through their normal specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I, Accordingly, under the authority
course of business or by the means
section 106, describes the authority of delegated to me by the Administrator,
identified in the ADDRESSES section.
the FAA Administrator. ‘‘Subtitle VII: the FAA proposes to amend 14 CFR part
FAA’s Determination and Requirements Aviation Programs,’’ describes in more 39 as follows:
of This Proposed AD detail the scope of the Agency’s
PART 39—AIRWORTHINESS
This product has been approved by authority.
We are issuing this rulemaking under DIRECTIVES
the aviation authority of another
country, and is approved for operation the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701: ■ 1. The authority citation for part 39
in the United States. Pursuant to our continues to read as follows:
bilateral agreement with the State of General requirements.’’ Under that
Design Authority, we have been notified section, Congress charges the FAA with Authority: 49 U.S.C. 106(g), 40113, 44701.
of the unsafe condition described in the promoting safe flight of civil aircraft in
§ 39.13 [Amended]
MCAI and service information air commerce by prescribing regulations
referenced above. We are proposing this for practices, methods, and procedures ■ 2. The FAA amends § 39.13 by
AD because we evaluated all pertinent the Administrator finds necessary for removing Airworthiness Directive (AD)
information and determined an unsafe safety in air commerce. This regulation 2016–23–01, Amendment 39–18708 (81
condition exists and is likely to exist or is within the scope of that authority FR 78899, November 10, 2016), and
develop on other products of the same because it addresses an unsafe condition adding the following new AD:
type design. that is likely to exist or develop on Airbus: Docket No. FAA–2018–0071; Product
products identified in this rulemaking Identifier 2017–NM–063–AD.
daltland on DSKBBV9HB2PROD with PROPOSALS
Explanation of Compliance Time action. (a) Comments Due Date
The compliance time for the This proposed AD is issued in
modification specified in this proposed accordance with authority delegated by We must receive comments by March 26,
AD for addressing WFD was established the Executive Director, Aircraft 2018.
to ensure that discrepant structure is Certification Service, as authorized by (b) Affected ADs
modified before WFD develops in FAA Order 8000.51C. In accordance This AD replaces AD 2016–23–01,
airplanes. Standard inspection with that order, issuance of ADs is Amendment 39–18708 (81 FR 78899,
techniques cannot be relied on to detect normally a function of the Compliance November 10, 2016) (‘‘AD 2016–23–01’’).
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![5584 Federal Register / Vol. 83, No. 27 / Thursday, February 8, 2018 / Proposed Rules
International Section, Transport Standards M–30, West Building Ground Floor, Discussion
Branch, FAA, 1601 Lind Avenue SW, Room W12–140, 1200 New Jersey
Renton, WA 98057–3356; telephone: 425– Fatigue damage can occur locally, in
Avenue SE, Washington, DC 20590. small areas or structural design details,
227–2125; fax: 425–227–1149.
(3) For service information identified in
• Hand Delivery: Deliver to Mail or globally, in widespread areas.
this AD, contact Airbus SAS, Airworthiness address above between 9 a.m. and 5 Multiple-site damage is widespread
Office—EAW, 1 Rond Point Maurice p.m., Monday through Friday, except damage that occurs in a large structural
Bellonte, 31707 Blagnac Cedex, France; Federal holidays. element such as a single rivet line of a
telephone: +33 5 61 93 36 96; fax: +33 5 61 For service information identified in lap splice joining two large skin panels.
93 44 51; email: account.airworth-eas@ this NPRM, contact Airbus SAS,
airbus.com; internet: http://www.airbus.com. Widespread damage can also occur in
Airworthiness Office—EAW, 1 Rond multiple elements such as adjacent
You may view this service information at the
Point Maurice Bellonte, 31707 Blagnac frames or stringers. Multiple-site
FAA, Transport Standards Branch, 1601 Lind
Avenue SW, Renton, WA. For information on Cedex, France; telephone: +33 5 61 93 damage and multiple-element damage
the availability of this material at the FAA, 36 96; fax: +33 5 61 93 44 51; email: cracks are typically too small initially to
call 425–227–1221. account.airworth-eas@airbus.com; be reliably detected with normal
Issued in Renton, Washington, on January
internet: http://www.airbus.com. You inspection methods. Without
25, 2018. may view this service information at the intervention, these cracks will grow,
Michael Kaszycki, FAA, Transport Standards Branch, 1601 and eventually compromise the
Lind Avenue SW, Renton, WA. For structural integrity of the airplane. This
Acting Director, System Oversight Division,
Aircraft Certification Service. information on the availability of this condition is known as widespread
material at the FAA, call 425–227–1221. fatigue damage. It is associated with
[FR Doc. 2018–02084 Filed 2–7–18; 8:45 am]
BILLING CODE 4910–13–P Examining the AD Docket general degradation of large areas of
structure with similar structural details
You may examine the AD docket on and stress levels. As an airplane ages,
the internet at http:// WFD will likely occur, and will
DEPARTMENT OF TRANSPORTATION
www.regulations.gov by searching for certainly occur if the airplane is
Federal Aviation Administration and locating Docket No. FAA–2018– operated long enough without any
0025; or in person at the Docket intervention.
14 CFR Part 39 Management Facility between 9 a.m. The FAA’s WFD final rule (75 FR
and 5 p.m., Monday through Friday, 69746, November 15, 2010) became
[Docket No. FAA–2018–0025; Product except Federal holidays. The AD docket
Identifier 2017–NM–101–AD] effective on January 14, 2011. The WFD
contains this NPRM, the regulatory rule requires certain actions to prevent
RIN 2120–AA64 evaluation, any comments received, and structural failure due to WFD
other information. The street address for throughout the operational life of
Airworthiness Directives; Airbus the Docket Operations office (telephone:
Airplanes certain existing transport category
800–647–5527) is in the ADDRESSES airplanes and all of these airplanes that
AGENCY: Federal Aviation section. Comments will be available in will be certificated in the future. For
Administration (FAA), DOT. the AD docket shortly after receipt. existing and future airplanes subject to
ACTION: Notice of proposed rulemaking FOR FURTHER INFORMATION CONTACT: Dan the WFD rule, the rule requires that
(NPRM). Rodina, Aerospace Engineer, DAHs establish a limit of validity (LOV)
International Section, Transport of the engineering data that support the
SUMMARY: We propose to adopt a new Standards Branch, FAA, 1601 Lind structural maintenance program.
airworthiness directive (AD) for all Avenue SW, Renton, WA 98057–3356; Operators affected by the WFD rule may
Airbus Model A310–203, –221, –222, telephone: 425–227–2125; fax: 425– not fly an airplane beyond its LOV,
–304, –322, –324, and –325 airplanes. 227–1149. unless an extended LOV is approved.
This proposed AD was prompted by a SUPPLEMENTARY INFORMATION: The WFD rule (75 FR 69746,
design approval holder (DAH) November 15, 2010) does not require
evaluation indicating that the outer Comments Invited identifying and developing maintenance
wing lower junction is subject to We invite you to send any written actions if the DAHs can show that such
widespread fatigue damage (WFD). This relevant data, views, or arguments about actions are not necessary to prevent
proposed AD would require modifying this proposed AD. Send your comments WFD before the airplane reaches the
the fastener holes at certain locations, to an address listed under the LOV. Many LOVs, however, do depend
which includes related investigative ADDRESSES section. Include ‘‘Docket No. on accomplishment of future
actions and applicable corrective FAA–2018–0025; Product Identifier maintenance actions. As stated in the
actions. We are proposing this AD to 2017–NM–101–AD’’ at the beginning of WFD rule, any maintenance actions
address the unsafe condition on these your comments. We specifically invite necessary to reach the LOV will be
products. comments on the overall regulatory, mandated by airworthiness directives
DATES: We must receive comments on economic, environmental, and energy through separate rulemaking actions.
this proposed AD by March 26, 2018. aspects of this NPRM. We will consider In the context of WFD, this action is
ADDRESSES: You may send comments, all comments received by the closing necessary to enable DAHs to propose
using the procedures found in 14 CFR date and may amend this NPRM based LOVs that allow operators the longest
daltland on DSKBBV9HB2PROD with PROPOSALS
11.43 and 11.45, by any of the following on those comments. operational lives for their airplanes, and
methods: We will post all comments we still ensure that WFD will not occur.
• Federal eRulemaking Portal: Go to receive, without change, to http:// This approach allows for an
http://www.regulations.gov. Follow the www.regulations.gov, including any implementation strategy that provides
instructions for submitting comments. personal information you provide. We flexibility to DAHs in determining the
• Fax: 202–493–2251. will also post a report summarizing each timing of service information
• Mail: U.S. Department of substantive verbal contact we receive development (with FAA approval),
Transportation, Docket Operations, about this NPRM. while providing operators with certainty
VerDate Sep<11>2014 16:37 Feb 07, 2018 Jkt 244001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\08FEP1.SGM 08FEP1](https://thefederalregister.org/doc/83_FR_5606/page/6.svg)
Document Created: 2018-02-08 00:16:19
Document Modified: 2018-02-08 00:16:19
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by March 26, 2018. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425- 227-1149. | |
| FR Citation | 83 FR 5579 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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