83 FR 8201 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 38 (February 26, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 38 (February 26, 2018)
| Page Range | 8201-8207 | |
| FR Document | 2018-03599 |
[Federal Register Volume 83, Number 38 (Monday, February 26, 2018)] [Proposed Rules] [Pages 8201-8207] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-03599] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0113; Product Identifier 2017-NM-060-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) 2016-12- 09, for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2016-12-09 requires removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that was found. Since we issued AD 2016-12-09, an evaluation by the design approval holder (DAH) indicates that certain fastener holes are subject to widespread fatigue damage (WFD). This proposed AD would add airplanes to the effectivity, add repetitive inspections of the fastener holes at frame (FR) 40, and, for certain airplanes, require a modification, which terminates the inspections. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by April 12, 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--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. 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- 0113; 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: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229. 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-2018-0113; Product Identifier 2017-NM-060-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We [[Page 8202]] will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 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 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 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. We issued AD 2016-12-09, Amendment 39-18558 (81 FR 38573, June 14, 2016) (``AD 2016-12-09''), for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2016-12-09 was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). AD 2016-12-09 requires removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that was found. We issued AD 2016-12-09 to detect and correct cracking on certain holes of the CWB, which could affect the structural integrity of the airplane. Actions Since AD 2016-12-09 Was Issued Since we issued AD 2016-12-09, an evaluation by the DAH indicates that the fastener holes at FR40 of the inside and outside CWB (above and below bottom skin) are subject to WFD. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0069, dated April 25, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes, and Model A340-200 and -300 series airplanes. The MCAI states: During accomplishment of A330 Airworthiness Limitation Item (ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between stringers (STR) 38 and STR39 on both LH [left-hand] and RH [right- hand] sides of the fuselage, cracks were found on an adjacent hole. After reaming at second oversize of the subject hole, the crack was still present. As a result of a sampling inspection program, additional crack findings were reported on this adjacent hole on other A330 and A340 aeroplanes. This condition, if not detected and corrected, could affect the structural integrity of the centre fuselage of the aeroplane. Prompted by these findings, EASA issued AD 2014-0149 [which corresponds to FAA AD 2016-12-09] to require removal of the fasteners and repetitive Special Detailed Inspection (SDI) of fastener holes at FR40 vertical web above or below Centre Wing Box (CWB) lower panel reference on both LH and RH sides of the fuselage, and, depending on findings, accomplishment of the applicable corrective actions. That [EASA] AD excluded certain aeroplanes from the Applicability, on which Airbus modification (mod) 55792 or mod 55306 had been embodied in production. Since EASA AD 2014-0149 was issued, prompted by complementary fatigue analyses correlated with in-service findings, Airbus published Service Bulletin (SB) A330-57-3115 Revision 01 and SB A340-57-4124 Revision 02, which introduced revised thresholds and intervals for the repetitive inspections of the inside CWB (above bottom skin), and an alleviation of the number of holes to be inspected, for post-mod 44360 and pre-mod 55306 configuration aeroplanes. In addition, for aeroplanes in post-mod 44360, post-mod 55306 and pre-mod 205225 configuration, Airbus developed mod 206051, introducing reinforcement of the structural integrity of the inside CWB (above bottom skin) area, and published associated Airbus SB A330-57-3129 and SB A340-57-4136, as applicable, which avoids the need for required repetitive inspections for the inside of the CWB. Finally, Airbus published SB A330-57-3116 Revision 01 and SB A330-57-4125 Revision 01, as applicable, to expand their Effectivity to include aeroplanes in post-mod 44360 and post-mod 49202 configuration for inspections of the outside CWB (below bottom skin), and introduced revised thresholds and intervals for the repetitive inspections of the outside CWB, and to provide an alleviation of the number of holes to be inspected. The repetitive inspection program for aeroplanes in pre-mod 44360 configuration remains unchanged. For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2014-0149, which is superseded, and requires new repetitive inspections of the fastener holes at FR40 of the inside and the outside CWB (above and below bottom skin), and the implementation of the modification of the inside CWB, as terminating action of the repetitive SDI. Required actions also include oversizing certain holes, installing new fasteners, and repairing any cracking that is found. The compliance times for the inspections range depending on airplane operation and utilization. The earliest initial flight-cycle compliance time is 13,500 flight cycles. The earliest initial flight- hour compliance time is 57,000 flight hours. The latest initial flight- cycle compliance time is 30,900 flight cycles. The latest initial flight-hour compliance time is 162,000 flight hours. The earliest repetitive flight-cycle compliance time is 5,950 flight cycles. The earliest repetitive flight-hour compliance time is 24,300 flight hours. The latest repetitive flight-cycle compliance time is 7,400 flight cycles. The latest repetitive flight-hour compliance time is 40,400 flight hours. 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-2018-0113. [[Page 8203]] Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. This service information describes procedures for removing the fasteners and doing a repetitive rototest inspection of fastener holes at FR40 vertical web on both sides, checking for the existence of a repair done as specified by a repair design approval sheet (RDAS), installing new fasteners in transition fit, oversizing the holes, and repairing any crack found. This service information is distinct because it applies to different airplane models and configurations. Airbus Service Bulletin A330-57-3114, Revision 01, dated January 13, 2017. Airbus Service Bulletin A330-57-3115, Revision 01, including Appendices 01 and 02, dated November 23, 2016. Airbus Service Bulletin A330-57-3116, Revision 01, including Appendices 01 and 02, dated November 23, 2016. Airbus Service Bulletin A340-57-4123, Revision 01, dated January 13, 2017. Airbus Service Bulletin A340-57-4124, Revision 02, including Appendices 01 and 02, dated November 23, 2016. Airbus Service Bulletin A340-57-4125, Revision 01, including Appendices 01 and 02, dated November 23, 2016. Airbus has also issued the following service information. This service information describes procedures for modification of certain fastener holes. The modification includes a rotating probe inspection for cracking, related investigative actions (checks of the hole diameter), and corrective actions (repair). This service information is distinct because it applies to different airplane models and configurations. Airbus Service Bulletin A330-57-3129, dated October 5, 2016. Airbus Service Bulletin A330-57-3130, dated November 23, 2016. Airbus Service Bulletin A330-57-3131, dated November 23, 2016. Airbus Service Bulletin A330-57-3132, including Appendices 01 and 02, dated November 23, 2016. Airbus Service Bulletin A340-57-4136, dated October 5, 2016. Airbus Service Bulletin A340-57-4137, dated November 23, 2016. Airbus Service Bulletin A340-57-4138, dated November 23, 2016. Airbus Service Bulletin A340-57-4139, including Appendices 01 and 02, dated November 23, 2016. 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. Explanation of a Certain Compliance Time The compliance time for the replacement specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is replaced 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 99 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection (retained actions 78 work-hours x $85 $0.................. $6,630 per $232,050 per from AD 2016-12-09) (35 per hour = $6,630 per inspection inspection airplanes). inspection cycle. cycle. cycle. Inspection (new proposed Up to 257 work-hours x $0.................. Up to $21,845 Up to $2,162,655 action) (99 airplanes). $85 per hour = per inspection per inspection $21,845 per cycle. cycle. inspection cycle. Modification (new proposed Up to 136 work-hours x Up to $1,070........ Up to $12,630... Up to action) (Up to 99 airplanes). $85 per hour = $1,250,370. $11,560. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary on-condition actions that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these actions: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product --------------------------------------------------------------------------------------------------------------- Oversize, installation, and Up to 105 work-hours Up to $21,560............ Up to $30,485............ inspection. x $85 per hour = $8,925. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition repairs specified in this proposed AD. 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 [[Page 8204]] 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) 2016-12-09, Amendment 39-18558 (81 FR 38573, June 14, 2016), and adding the following new AD: Airbus: Docket No. FAA-2018-0113; Product Identifier 2017-NM-060-AD. (a) Comments Due Date We must receive comments by April 12, 2018. (b) Affected ADs This AD replaces AD 2016-12-09, Amendment 39-18558 (81 FR 38573, June 14, 2016) (``AD 2016-12-09''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Repair Instructions R57115092 have been embodied in service on both right- hand (RH) and left-hand (LH) sides. (1) Model A330-201, -202, -203, -223, and -243 airplanes. (2) Model A330-223F and -243F airplanes. (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (4) Model A340-211, -212, and -213 airplanes. (5) Model A340-311, -312, and -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). We are issuing this AD to detect and correct cracking of certain holes of certain frames of the CWB, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Service Information (1) For the actions required by paragraphs (h), (i), and (j) of this AD, use the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(vi) of this AD. (i) Airbus Service Bulletin A330-57-3114, Revision 01, dated January 13, 2017 (CWB inspection area: Below) (for Model A330-300 series airplanes in pre-modification 44360 configuration). (ii) Airbus Service Bulletin A330-57-3115, Revision 01, including Appendices 01 and 02, dated November 23, 2016 (CWB inspection area: Above) (for Model A330-200 and -300 series airplanes in pre-modification 55306 and pre-modification 55792 configuration). (iii) Airbus Service Bulletin A330-57-3116, Revision 01, including Appendices 01 and 02, dated November 23, 2016 (CWB inspection area: Below) (for Model A330-200 and -300 series airplanes in post-modification 44360 configuration). (iv) Airbus Service Bulletin A340-57-4123, Revision 01, dated January 13, 2017 (CWB inspection area: Below) (for Model A340-200 and -300 series airplanes in pre-modification 44360 configuration). (v) Airbus Service Bulletin A340-57-4124, Revision 02, including Appendices 01 and 02, dated November 23, 2016 (CWB inspection area: Above) (for Model A340-200 and -300 series airplanes in pre- modification 55306 and pre-modification 55792 configuration). (vi) Airbus Service Bulletin A340-57-4125, Revision 01, including Appendices 01 and 02, dated November 23, 2016 (CWB inspection area: Below) (for Model A340-200 and -300 series airplanes in post-modification 44360 configuration). (2) For the modification required by paragraph (o)(1) of this AD, use the applicable service information specified in paragraphs (g)(2)(i) through (g)(2)(vi) of this AD. (i) Airbus Service Bulletin A330-57-3130, dated November 23, 2016 (for Model A330-200 and -300 series airplanes in post- modification 44360, post-Airbus Service Bulletin A330-57-3131, and pre-modification 49202 configuration). (ii) Airbus Service Bulletin A330-57-3131, dated November 23, 2016 (for Model A330-200 and -300 series airplanes in post- modification 44360 and pre-modification 55306 configuration). (iii) Airbus Service Bulletin A330-57-3132, including Appendices 01 and 02, dated November 23, 2016 (for Model A330-200 and -300 series airplanes in post-modification 44360 configuration). (iv) Airbus Service Bulletin A340-57-4137, dated November 23, 2016 (for Model A340-200 and -300 series airplanes in post- modification 44360, post-Airbus Service Bulletin A340-57-4138, and pre-modification 49202 configuration). (v) Airbus Service Bulletin A340-57-4138, dated November 23, 2016 (for Model A340-200 and -300 series airplanes in post- modification 44360 and pre-modification 55306 configuration). (vi) Airbus Service Bulletin A340-57-4139, including Appendices 01 and 02, dated November 23, 2016 (for Model A340-200 and -300 series airplanes in post-modification 44360 configuration). (h) Repetitive Inspections and Certain Repairs Except as specified in paragraphs (l)(2), (l)(3), (p) of this AD: Before exceeding the applicable threshold specified in paragraph 1.E., ``Compliance'' of the applicable service information specified in paragraph (g)(1) of this AD, or within the compliance time specified in table 1 to paragraph (h) of this AD, whichever occurs later; remove the fasteners and accomplish a special detailed inspection (SDI) of the fastener holes at frame (FR) 40 vertical web, on both LH and RH sides, of the affected CWB lower panel area, and, as applicable, check for the existence of a repair done as specified by a repair design approval sheet (RDAS), in accordance with the Accomplishment Instructions of the [[Page 8205]] applicable service information specified in paragraph (g)(1) of this AD, and if any RDAS repair is found before further flight, repair 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. Repeat the SDI thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of the applicable service information identified in paragraph (g)(1) of this AD. [GRAPHIC] [TIFF OMITTED] TP26FE18.000 (i) Follow-On Actions: No Cracking If no crack is found during any inspection required by paragraph (h) of this AD: Before further flight, install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) of this AD. (j) Follow-On Actions: Cracking If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, oversize the holes to the first oversize in comparison with the current hole diameter, and do an SDI for cracks, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1) of this AD. (1) If no cracking is found during the SDI required by the introductory text of paragraph (j) of this AD: Before further flight, install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1) of this AD. (2) If any cracking is found during the SDI required by the introductory text of paragraph (j) of this AD: Before further flight, repair 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. (k) No Reporting Required Although the applicable service information specified in paragraph (g)(1) of this AD specifies to submit certain information to the manufacturer, and specifies that action as ``RC'' (Required for Compliance), this AD does not include that requirement. (l) Exceptions to Service Information (1) Where the applicable service information identified in paragraphs (g) and (m) of this AD specifies contacting Airbus for appropriate action: Before further flight, repair 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. (2) Where paragraph 1.E., ``Compliance,'' of the applicable service information specified in paragraph (g)(1) of this AD specifies a compliance time in terms of a ``Threshold'' and ``Grace Period,'' this AD requires compliance at the later of the applicable threshold and grace period. (3) When it is determined that no RDAS is found to exist for the FR40 area it is acceptable to accomplish the first SDI before exceeding the applicable threshold, instead of ``before next flight'', as specified in the applicable service information specified in paragraph (g)(1)(ii), (g)(1)(iii), (g)(1)(v) and (g)(1)(vi) of this AD. (m) Modification for Airplanes in Post-Modification 55306 and Pre- Modification 205225 Configuration For airplanes in post-modification 55306 and pre-modification 205225 configuration: Before exceeding the applicable compliance time specified in table 2 to paragraph (m) of this AD, as applicable, or within 18 months after the effective date of this AD, whichever occurs later; modify the inside CWB (above bottom skin), including doing a rotating probe inspection for cracking and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3129, dated October 5, 2016; or Airbus Service Bulletin A340-57-4136, dated October 5, 2016; as applicable; except as required by paragraph (l)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. [[Page 8206]] [GRAPHIC] [TIFF OMITTED] TP26FE18.001 (n) Terminating Action for Certain Airworthiness Limitation Item (ALI) Tasks (1) Accomplishment on an airplane of the initial and repetitive inspections required by paragraph (h) of this AD terminates the requirements of ALI task 57-11-02 and task 57-11-04 of the applicable Airbus Airworthiness Limitation Section (ALS) Part 2, Damage Tolerant (DT) ALI, for that airplane. (2) Modification of an airplane as required by paragraph (m) of this AD terminates the requirements of ALI task 57-11-02 of the applicable Airbus ALS Part 2, DT ALI, for that airplane. (o) Terminating Action for Repetitive SDI Inspections (1) Modification of a post-modification 44360 airplane by multiple cold working, including doing a rotating probe inspection for cracking and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraph (g)(2) of this AD, except as required by paragraph (l)(1) of this AD, constitutes terminating action for the repetitive SDI required by paragraph (h) of this AD for that airplane, provided the modification is accomplished within the applicable compliance times specified in the applicable Airbus service information specified in paragraph (g)(1) of this AD. (2) If, during any inspection of a post-modification 44360 airplane, as required by paragraph (h) of this AD, a crack previously repaired by an Airbus RDAS is detected only on the LH or RH side, it is permitted to do the modification specified in paragraph (o)(1) of this AD on the non-repaired side. Doing the modification constitutes terminating action for the repetitive SDI required by paragraph (h) of this AD on the modified side only. (p) Extension to Compliance Time for Certain Airplanes For post-modification 44360 airplanes and pre-modification 55306 airplanes that have been inspected before the effective date of this AD as required by AD 2016-12-09: It is permitted to defer the next due inspection to 18 months after the effective date of this AD, provided the previous inspection interval, as applicable, depending on airplane configuration and utilization, as specified in the service information used in the previous inspection is not exceeded. (q) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraphs (h) through (j) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (q)(1)(i) through (q)(1)(vi) of this AD. This service information was incorporated by reference in AD 2016-09-11, Amendment 39-18509 (81 FR 27986, May 9, 2016). (i) Airbus Service Bulletin A330-57-3114, dated March 12, 2013. (ii) Airbus Service Bulletin A330-57-3115, April 4, 2013. (iii) Airbus Service Bulletin A330-57-3116, dated March 12, 2013. (iv) Airbus Service Bulletin A340-57-4123, dated March 12, 2013. (v) Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. (vi) Airbus Service Bulletin A340-57-4125, dated March 12, 2013. (2) This paragraph provides credit for the actions required by paragraphs (h) through (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A340-57-4124, dated April 4, 2013. This service information is not incorporated by reference in this AD. (3) This paragraph provides credit for the actions required by paragraphs (h) through (j) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (q)(3)(i) through (q)(3)(viii) of this AD. This service information is not incorporated by reference in this AD. (i) Airbus Technical Disposition LR57D11023270, Issue B, dated July 12, 2011. (ii) Airbus Technical Disposition LR57D11029170, Issue C, dated September 6, 2011. (iii) Airbus Technical Disposition LR57D11029171, Issue B, dated September 6, 2011. (iv) Airbus Technical Disposition LR57D11029172, Issue B, dated September 6, 2011. (v) Airbus Technical Disposition LR57D11029173, Issue B, dated September 6, 2011. (vi) Airbus Technical Disposition LR57D11023714, Issue B, dated July 12, 2011. (vii) Airbus Technical Disposition LR57D11030740, Issue C, dated September 22, 2011. (viii) Airbus Technical Disposition LR57D11030741, Issue B, dated September 22, 2011. (r) Other FAA AD Provisions The following provisions also apply to this AD: (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 manager of the International Section, send it to the attention of the person identified in paragraph (s)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate [[Page 8207]] 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): Except as required by paragraphs (k) and (l)(1) of this AD: 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. (s) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0069, dated April 25, 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-2018-0113. (2) For more information about this AD, contact, Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Issued in Renton, Washington, on February 14, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-03599 Filed 2-23-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 38 / Monday, February 26, 2018 / Proposed Rules 8201
of this service bulletin,’’ this AD requires MC 110–SK57, Seal Beach, CA 90740–5600; • Mail: U.S. Department of
using ‘‘the effective date of this AD.’’ telephone 562–797–1717; internet https:// Transportation, Docket Operations,
www.myboeingfleet.com. You may view this M–30, West Building Ground Floor,
(i) Credit for Previous Actions
service information at the FAA, Transport
This paragraph provides credit for the Room W12–140, 1200 New Jersey
Standards Branch, 2200 South 216th St., Des
corresponding actions specified in paragraph Moines, WA. For information on the Avenue SE, Washington, DC 20590.
(g) of this AD, if those actions were availability of this material at the FAA, call • Hand Delivery: Deliver to Mail
performed before the effective date of this AD 206–231–3195. address above between 9 a.m. and 5
using Boeing Special Attention Service p.m., Monday through Friday, except
Bulletin 777–25–0621, dated December 10, Issued in Renton, Washington, on February
15, 2018. Federal holidays.
2014. For service information identified in
Michael Kaszycki,
(j) Alternative Methods of Compliance this NPRM, contact Airbus SAS,
(AMOCs) Acting Director, System Oversight Division,
Airworthiness Office—EAL, 1 Rond
Aircraft Certification Service.
(1) The Manager, Seattle ACO Branch, Point Maurice Bellonte, 31707 Blagnac
[FR Doc. 2018–03712 Filed 2–23–18; 8:45 am]
FAA, has the authority to approve AMOCs Cedex, France; telephone: +33 5 61 93
for this AD, if requested using the procedures BILLING CODE 4910–13–P 36 96; fax: +33 5 61 93 45 80; email:
found in 14 CFR 39.19. In accordance with airworthiness.A330-A340@airbus.com;
14 CFR 39.19, send your request to your internet: http://www.airbus.com. You
principal inspector or local Flight Standards DEPARTMENT OF TRANSPORTATION
District Office, as appropriate. If sending
may view this referenced service
information directly to the manager of the Federal Aviation Administration information at the FAA, Transport
certification office, send it to the attention of Standards Branch, 2200 South 216th St.,
the person identified in paragraph (k)(1) of 14 CFR Part 39 Des Moines, WA. For information on the
this AD. Information may be emailed to: 9- availability of this material at the FAA,
ANM-Seattle-ACO-AMOC-Requests@faa.gov. [Docket No. FAA–2018–0113; Product call 206–231–3195.
(2) Before using any approved AMOC, Identifier 2017–NM–060–AD]
notify your appropriate principal inspector, Examining the AD Docket
or lacking a principal inspector, the manager RIN 2120–AA64
You may examine the AD docket on
of the local flight standards district office/
certificate holding district office. Airworthiness Directives; Airbus the internet at http://
(3) An AMOC that provides an acceptable Airplanes www.regulations.gov by searching for
level of safety may be used for any repair, and locating Docket No. FAA–2018–
modification, or alteration required by this AGENCY: Federal Aviation 0113; or in person at the Docket
AD if it is approved by the Boeing Administration (FAA), DOT. Management Facility between 9 a.m.
Commercial Airplanes Organization ACTION: Notice of proposed rulemaking and 5 p.m., Monday through Friday,
Designation Authorization (ODA) that has (NPRM). except Federal holidays. The AD docket
been authorized by the Manager, Seattle ACO contains this proposed AD, the
Branch, to make those findings. To be SUMMARY: We propose to supersede regulatory evaluation, any comments
approved, the repair method, modification
deviation, or alteration deviation must meet
Airworthiness Directive (AD) 2016–12– received, and other information. The
the certification basis of the airplane, and the 09, for certain Airbus Model A330–200, street address for the Docket Operations
approval must specifically refer to this AD. –200 Freighter, and –300 series office (telephone: 800–647–5527) is in
(4) For service information that contains airplanes; and Model A340–200 and the ADDRESSES section. Comments will
steps that are labeled as RC, the provisions –300 series airplanes. AD 2016–12–09 be available in the AD docket shortly
of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD requires removing fasteners, doing a after receipt.
apply. rototest inspection of fastener holes,
(i) The steps labeled as RC, including FOR FURTHER INFORMATION CONTACT:
installing new fasteners, oversizing the Vladimir Ulyanov, Aerospace Engineer,
substeps under an RC step and any figures
identified in an RC step, must be done to
holes and doing rototest inspections for International Section, Transport
comply with the AD. If a step or substep is cracks if necessary, and repairing any Standards Branch, FAA, 2200 South
labeled ‘‘RC Exempt,’’ then the RC cracking that was found. Since we 216th St., Des Moines, WA 98198;
requirement is removed from that step or issued AD 2016–12–09, an evaluation telephone and fax: 206–231–3229.
substep. An AMOC is required for any by the design approval holder (DAH)
SUPPLEMENTARY INFORMATION:
deviations to RC steps, including substeps indicates that certain fastener holes are
and identified figures. subject to widespread fatigue damage Comments Invited
(ii) Steps not labeled as RC may be (WFD). This proposed AD would add
deviated from using accepted methods in We invite you to send any written
airplanes to the effectivity, add relevant data, views, or arguments about
accordance with the operator’s maintenance
or inspection program without obtaining repetitive inspections of the fastener this proposed AD. Send your comments
approval of an AMOC, provided the RC steps, holes at frame (FR) 40, and, for certain to an address listed under the
including substeps and identified figures, can airplanes, require a modification, which ADDRESSES section. Include ‘‘Docket No.
still be done as specified, and the airplane terminates the inspections. We are FAA–2018–0113; Product Identifier
can be put back in an airworthy condition. proposing this AD to address the unsafe 2017–NM–060–AD’’ at the beginning of
(k) Related Information condition on these products. your comments. We specifically invite
(1) For more information about this AD, DATES: We must receive comments on comments on the overall regulatory,
contact Scott Craig, Aerospace Engineer, this proposed AD by April 12, 2018. economic, environmental, and energy
daltland on DSKBBV9HB2PROD with PROPOSALS
Cabin Safety and Environmental Systems ADDRESSES: You may send comments, aspects of this proposed AD. We will
Section, FAA, Seattle ACO Branch, 2200 using the procedures found in 14 CFR consider all comments received by the
South 216th Street, Des Moines, WA 98198; 11.43 and 11.45, by any of the following closing date and may amend this
phone and fax: 206–231–3566; email:
Michael.S.Craig@faa.gov.
methods: proposed AD based on those comments.
(2) For service information identified in • Federal eRulemaking Portal: Go to We will post all comments we
this AD, contact Boeing Commercial http://www.regulations.gov. Follow the receive, without change, to http://
Airplanes, Attention: Contractual & Data instructions for submitting comments. www.regulations.gov, including any
Services (C&DS), 2600 Westminster Blvd., • Fax: 202–493–2251. personal information you provide. We
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![8202 Federal Register / Vol. 83, No. 38 / Monday, February 26, 2018 / Proposed Rules
will also post a report summarizing each while providing operators with certainty Since EASA AD 2014–0149 was issued,
substantive verbal contact we receive regarding the LOV applicable to their prompted by complementary fatigue analyses
about this proposed AD. airplanes. correlated with in-service findings, Airbus
We issued AD 2016–12–09, published Service Bulletin (SB) A330–57–
Discussion Amendment 39–18558 (81 FR 38573, 3115 Revision 01 and SB A340–57–4124
Fatigue damage can occur locally, in June 14, 2016) (‘‘AD 2016–12–09’’), for Revision 02, which introduced revised
small areas or structural design details, certain Airbus Model A330–200, –200 thresholds and intervals for the repetitive
or globally, in widespread areas. Freighter, and –300 series airplanes, and inspections of the inside CWB (above bottom
Multiple-site damage is widespread skin), and an alleviation of the number of
Model A340–200 and –300 series
damage that occurs in a large structural holes to be inspected, for post-mod 44360
airplanes. AD 2016–12–09 was
and pre-mod 55306 configuration aeroplanes.
element such as a single rivet line of a prompted by reports that cracks were In addition, for aeroplanes in post-mod
lap splice joining two large skin panels. found on an adjacent hole of certain 44360, post-mod 55306 and pre-mod 205225
Widespread damage can also occur in frames of the center wing box (CWB). configuration, Airbus developed mod
multiple elements such as adjacent AD 2016–12–09 requires removing 206051, introducing reinforcement of the
frames or stringers. Multiple-site fasteners, doing a rototest inspection of structural integrity of the inside CWB (above
damage and multiple-element damage fastener holes, installing new fasteners, bottom skin) area, and published associated
cracks are typically too small initially to oversizing the holes and doing rototest Airbus SB A330–57–3129 and SB A340–57–
be reliably detected with normal inspections for cracks if necessary, and 4136, as applicable, which avoids the need
inspection methods. Without repairing any cracking that was found. for required repetitive inspections for the
intervention, these cracks will grow, We issued AD 2016–12–09 to detect and inside of the CWB.
and eventually compromise the correct cracking on certain holes of the Finally, Airbus published SB A330–57–
structural integrity of the airplane. This CWB, which could affect the structural 3116 Revision 01 and SB A330–57–4125
condition is known as WFD. It is integrity of the airplane. Revision 01, as applicable, to expand their
associated with general degradation of Effectivity to include aeroplanes in post-mod
large areas of structure with similar Actions Since AD 2016–12–09 Was 44360 and post-mod 49202 configuration for
structural details and stress levels. As Issued inspections of the outside CWB (below
an airplane ages, WFD will likely occur, Since we issued AD 2016–12–09, an bottom skin), and introduced revised
evaluation by the DAH indicates that thresholds and intervals for the repetitive
and will certainly occur if the airplane
inspections of the outside CWB, and to
is operated long enough without any the fastener holes at FR40 of the inside
provide an alleviation of the number of holes
intervention. and outside CWB (above and below
to be inspected. The repetitive inspection
The FAA’s WFD final rule (75 FR bottom skin) are subject to WFD. program for aeroplanes in pre-mod 44360
69746, November 15, 2010) became The European Aviation Safety Agency configuration remains unchanged.
effective on January 14, 2011. The WFD (EASA), which is the Technical Agent For the reasons described above, this
rule requires certain actions to prevent for the Member States of the European [EASA] AD partially retains the requirements
structural failure due to WFD Union, has issued EASA AD 2017–0069, of EASA AD 2014–0149, which is
throughout the operational life of dated April 25, 2017 (referred to after superseded, and requires new repetitive
certain existing transport category this as the Mandatory Continuing inspections of the fastener holes at FR40 of
airplanes and all of these airplanes that Airworthiness Information, or ‘‘the the inside and the outside CWB (above and
will be certificated in the future. For MCAI’’), to correct an unsafe condition below bottom skin), and the implementation
existing and future airplanes subject to for certain Airbus Model A330–200, of the modification of the inside CWB, as
the WFD rule, the rule requires that –200 Freighter, and –300 series terminating action of the repetitive SDI.
DAHs establish a limit of validity (LOV) airplanes, and Model A340–200 and
–300 series airplanes. The MCAI states: Required actions also include
of the engineering data that support the
oversizing certain holes, installing new
structural maintenance program. During accomplishment of A330 fasteners, and repairing any cracking
Operators affected by the WFD rule may Airworthiness Limitation Item (ALI) task 57–
that is found.
not fly an airplane beyond its LOV, 11–04 on the rear fitting of the Frame (FR)
unless an extended LOV is approved. 40 between stringers (STR) 38 and STR39 on The compliance times for the
The WFD rule does not require both LH [left-hand] and RH [right-hand] sides inspections range depending on
identifying and developing maintenance of the fuselage, cracks were found on an airplane operation and utilization. The
adjacent hole. After reaming at second earliest initial flight-cycle compliance
actions if the DAHs can show that such oversize of the subject hole, the crack was
actions are not necessary to prevent still present. As a result of a sampling
time is 13,500 flight cycles. The earliest
WFD before the airplane reaches the inspection program, additional crack findings initial flight-hour compliance time is
LOV. Many LOVs, however, do depend were reported on this adjacent hole on other 57,000 flight hours. The latest initial
on accomplishment of future A330 and A340 aeroplanes. flight-cycle compliance time is 30,900
maintenance actions. As stated in the This condition, if not detected and flight cycles. The latest initial flight-
WFD rule, any maintenance actions corrected, could affect the structural integrity hour compliance time is 162,000 flight
necessary to reach the LOV will be of the centre fuselage of the aeroplane. hours. The earliest repetitive flight-cycle
Prompted by these findings, EASA issued
mandated by airworthiness directives AD 2014–0149 [which corresponds to FAA
compliance time is 5,950 flight cycles.
through separate rulemaking actions. AD 2016–12–09] to require removal of the The earliest repetitive flight-hour
In the context of WFD, this action is fasteners and repetitive Special Detailed compliance time is 24,300 flight hours.
necessary to enable DAHs to propose Inspection (SDI) of fastener holes at FR40 The latest repetitive flight-cycle
daltland on DSKBBV9HB2PROD with PROPOSALS
LOVs that allow operators the longest vertical web above or below Centre Wing Box compliance time is 7,400 flight cycles.
operational lives for their airplanes, and (CWB) lower panel reference on both LH and The latest repetitive flight-hour
still ensure that WFD will not occur. RH sides of the fuselage, and, depending on compliance time is 40,400 flight hours.
This approach allows for an findings, accomplishment of the applicable You may examine the MCAI in the AD
corrective actions. That [EASA] AD excluded
implementation strategy that provides certain aeroplanes from the Applicability, on docket on the internet at http://
flexibility to DAHs in determining the which Airbus modification (mod) 55792 or www.regulations.gov by searching for
timing of service information mod 55306 had been embodied in and locating Docket No. FAA–2018–
development (with FAA approval), production. 0113.
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![8204 Federal Register / Vol. 83, No. 38 / Monday, February 26, 2018 / Proposed Rules
promoting safe flight of civil aircraft in § 39.13 [Amended] and –300 series airplanes in post-
air commerce by prescribing regulations modification 44360 configuration).
■ 2. The FAA amends § 39.13 by (iv) Airbus Service Bulletin A340–57–
for practices, methods, and procedures removing Airworthiness Directive (AD) 4123, Revision 01, dated January 13, 2017
the Administrator finds necessary for 2016–12–09, Amendment 39–18558 (81 (CWB inspection area: Below) (for Model
safety in air commerce. This regulation FR 38573, June 14, 2016), and adding A340–200 and –300 series airplanes in pre-
is within the scope of that authority the following new AD: modification 44360 configuration).
because it addresses an unsafe condition (v) Airbus Service Bulletin A340–57–4124,
that is likely to exist or develop on Airbus: Docket No. FAA–2018–0113; Product Revision 02, including Appendices 01 and
products identified in this rulemaking Identifier 2017–NM–060–AD. 02, dated November 23, 2016 (CWB
action. (a) Comments Due Date inspection area: Above) (for Model A340–200
and –300 series airplanes in pre-modification
This proposed AD is issued in We must receive comments by April 12, 55306 and pre-modification 55792
accordance with authority delegated by 2018. configuration).
the Executive Director, Aircraft (b) Affected ADs (vi) Airbus Service Bulletin A340–57–
Certification Service, as authorized by 4125, Revision 01, including Appendices 01
This AD replaces AD 2016–12–09,
FAA Order 8000.51C. In accordance Amendment 39–18558 (81 FR 38573, June
and 02, dated November 23, 2016 (CWB
with that order, issuance of ADs is 14, 2016) (‘‘AD 2016–12–09’’).
inspection area: Below) (for Model A340–200
normally a function of the Compliance and –300 series airplanes in post-
and Airworthiness Division, but during (c) Applicability modification 44360 configuration).
this transition period, the Executive This AD applies to the Airbus airplanes (2) For the modification required by
identified in paragraphs (c)(1) through (c)(5) paragraph (o)(1) of this AD, use the
Director has delegated the authority to applicable service information specified in
issue ADs applicable to transport of this AD, certificated in any category, all
manufacturer serial numbers, except those on paragraphs (g)(2)(i) through (g)(2)(vi) of this
category airplanes to the Director of the AD.
which Airbus Repair Instructions R57115092
System Oversight Division. have been embodied in service on both right- (i) Airbus Service Bulletin A330–57–3130,
hand (RH) and left-hand (LH) sides. dated November 23, 2016 (for Model A330–
Regulatory Findings 200 and –300 series airplanes in post-
(1) Model A330–201, –202, –203, –223, and
We determined that this proposed AD –243 airplanes. modification 44360, post-Airbus Service
would not have federalism implications (2) Model A330–223F and –243F airplanes. Bulletin A330–57–3131, and pre-
(3) Model A330–301, –302, –303, –321, modification 49202 configuration).
under Executive Order 13132. This
–322, –323, –341, –342, and –343 airplanes. (ii) Airbus Service Bulletin A330–57–3131,
proposed AD would not have a dated November 23, 2016 (for Model A330–
substantial direct effect on the States, on (4) Model A340–211, –212, and –213
airplanes. 200 and –300 series airplanes in post-
the relationship between the national modification 44360 and pre-modification
(5) Model A340–311, –312, and –313
Government and the States, or on the airplanes. 55306 configuration).
distribution of power and (iii) Airbus Service Bulletin A330–57–
responsibilities among the various (d) Subject 3132, including Appendices 01 and 02, dated
levels of government. Air Transport Association (ATA) of November 23, 2016 (for Model A330–200 and
America Code 57, Wings. –300 series airplanes in post-modification
For the reasons discussed above, I 44360 configuration).
certify this proposed regulation: (e) Reason (iv) Airbus Service Bulletin A340–57–
1. Is not a ‘‘significant regulatory This AD was prompted by reports that 4137, dated November 23, 2016 (for Model
action’’ under Executive Order 12866; cracks were found on an adjacent hole of A340–200 and –300 series airplanes in post-
2. Is not a ‘‘significant rule’’ under the certain frames of the center wing box (CWB). modification 44360, post-Airbus Service
We are issuing this AD to detect and correct Bulletin A340–57–4138, and pre-
DOT Regulatory Policies and Procedures
cracking of certain holes of certain frames of modification 49202 configuration).
(44 FR 11034, February 26, 1979); (v) Airbus Service Bulletin A340–57–4138,
the CWB, which could affect the structural
3. Will not affect intrastate aviation in integrity of the airplane. dated November 23, 2016 (for Model A340–
Alaska; and 200 and –300 series airplanes in post-
(f) Compliance modification 44360 and pre-modification
4. Will not have a significant
economic impact, positive or negative, Comply with this AD within the 55306 configuration).
compliance times specified, unless already (vi) Airbus Service Bulletin A340–57–
on a substantial number of small entities
done. 4139, including Appendices 01 and 02, dated
under the criteria of the Regulatory November 23, 2016 (for Model A340–200 and
Flexibility Act. (g) Service Information –300 series airplanes in post-modification
(1) For the actions required by paragraphs 44360 configuration).
List of Subjects in 14 CFR Part 39
(h), (i), and (j) of this AD, use the applicable
service information specified in paragraphs (h) Repetitive Inspections and Certain
Air transportation, Aircraft, Aviation Repairs
safety, Incorporation by reference, (g)(1)(i) through (g)(1)(vi) of this AD.
Safety. (i) Airbus Service Bulletin A330–57–3114, Except as specified in paragraphs (l)(2),
Revision 01, dated January 13, 2017 (CWB (l)(3), (p) of this AD: Before exceeding the
The Proposed Amendment inspection area: Below) (for Model A330–300 applicable threshold specified in paragraph
series airplanes in pre-modification 44360 1.E., ‘‘Compliance’’ of the applicable service
Accordingly, under the authority configuration). information specified in paragraph (g)(1) of
delegated to me by the Administrator, (ii) Airbus Service Bulletin A330–57–3115, this AD, or within the compliance time
the FAA proposes to amend 14 CFR part Revision 01, including Appendices 01 and specified in table 1 to paragraph (h) of this
daltland on DSKBBV9HB2PROD with PROPOSALS
39 as follows: 02, dated November 23, 2016 (CWB AD, whichever occurs later; remove the
inspection area: Above) (for Model A330–200 fasteners and accomplish a special detailed
PART 39—AIRWORTHINESS and –300 series airplanes in pre-modification inspection (SDI) of the fastener holes at frame
DIRECTIVES 55306 and pre-modification 55792 (FR) 40 vertical web, on both LH and RH
configuration). sides, of the affected CWB lower panel area,
(iii) Airbus Service Bulletin A330–57– and, as applicable, check for the existence of
■ 1. The authority citation for part 39
3116, Revision 01, including Appendices 01 a repair done as specified by a repair design
continues to read as follows: and 02, dated November 23, 2016 (CWB approval sheet (RDAS), in accordance with
Authority: 49 U.S.C. 106(g), 40113, 44701. inspection area: Below) (for Model A330–200 the Accomplishment Instructions of the
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![Federal Register / Vol. 83, No. 38 / Monday, February 26, 2018 / Proposed Rules 8207
principal inspector, or lacking a principal DEPARTMENT OF TRANSPORTATION Authority for This Rulemaking
inspector, the manager of the local flight
The FAA’s authority to issue rules
standards district office/certificate holding Federal Aviation Administration
district office.
regarding aviation safety is found in
(2) Contacting the Manufacturer: As of the
Title 49 of the United States Code.
14 CFR Part 71
effective date of this AD, for any requirement
Subtitle I, Section 106 describes the
in this AD to obtain corrective actions from authority of the FAA Administrator.
[Docket No. FAA–2017–1088; Airspace Subtitle VII, Aviation Programs,
a manufacturer, the action must be Docket No. 17–AWP–25]
accomplished using a method approved by describes in more detail the scope of the
the Manager, International Section, Transport Proposed Revocation of Class E agency’s authority. This rulemaking is
Standards Branch, FAA; or EASA; or Airspace; Crows Landing, CA promulgated under the authority
Airbus’s EASA DOA. If approved by the described in Subtitle VII, Part A,
DOA, the approval must include the DOA- AGENCY: Federal Aviation Subpart I, Section 40103. Under that
authorized signature. Administration (FAA), DOT. section, the FAA is charged with
(3) Required for Compliance (RC): Except ACTION: Notice of proposed rulemaking prescribing regulations to assign the use
as required by paragraphs (k) and (l)(1) of this (NPRM). of airspace necessary to ensure the
AD: If any service information contains safety of aircraft and the efficient use of
procedures or tests that are identified as RC, SUMMARY: This action proposes to airspace. This regulation is within the
those procedures and tests must be done to remove Class E airspace extending scope of that authority as it clarifies
comply with this AD; any procedures or tests upward from 1,200 feet above the airspace designations by eliminating the
that are not identified as RC are surface at Crows Landing Airport, redundancy.
recommended. Those procedures and tests Crows Landing, CA. This airspace is
Comments Invited
that are not identified as RC may be deviated wholly contained within the
from using accepted methods in accordance Sacramento en route airspace area and Interested parties are invited to
with the operator’s maintenance or duplication is not necessary. participate in this proposed rulemaking
inspection program without obtaining DATES: Comments must be received on by submitting such written data, views,
approval of an AMOC, provided the or before April 12, 2018. or arguments, as they may desire.
procedures and tests identified as RC can be Comments that provide the factual basis
ADDRESSES: Send comments on this
done and the airplane can be put back in an supporting the views and suggestions
proposal to the U.S. Department of
airworthy condition. Any substitutions or presented are particularly helpful in
Transportation, Docket Operations, 1200
changes to procedures or tests identified as developing reasoned regulatory
New Jersey Avenue SE, West Building,
RC require approval of an AMOC. decisions on the proposal. Comments
Ground Floor, Room W12–140,
are specifically invited on the overall
(s) Related Information Washington, DC 20590; telephone: (800)
regulatory, aeronautical, economic,
(1) Refer to Mandatory Continuing 647–5527, or (202) 366–9826. You must
environmental, and energy-related
Airworthiness Information (MCAI) EASA AD identify FAA Docket No. FAA–2017–
aspects of the proposal.
2017–0069, dated April 25, 2017, for related 1088; Airspace Docket No. 17–AWP–25,
Communications should identify both
information. This MCAI may be found in the at the beginning of your comments. You
docket numbers (Docket No. FAA–
AD docket on the internet at http:// may also submit comments through the
2017–1088; Airspace Docket No. 17–
www.regulations.gov by searching for and internet at http://www.regulations.gov.
AWP–25) and be submitted in triplicate
locating Docket No. FAA–2018–0113. FAA Order 7400.11B, Airspace
to DOT Docket Operations (see
(2) For more information about this AD, Designations and Reporting Points, and
ADDRESSES section for address and
contact, Vladimir Ulyanov, Aerospace subsequent amendments can be viewed
phone number). You may also submit
Engineer, International Section, Transport online at http://www.faa.gov/air_traffic/
comments through the internet at http://
Standards Branch, FAA, 2200 South 216th publications/. For further information,
www.regulations.gov.
St., Des Moines, WA 98198; telephone and you can contact the Airspace Policy
Persons wishing the FAA to
fax: 206–231–3229. Group, Federal Aviation
acknowledge receipt of their comments
(3) For service information identified in Administration, 800 Independence
on this notice must submit with those
this AD, contact Airbus SAS, Airworthiness Avenue SW, Washington, DC 20591;
comments a self-addressed, stamped
Office—EAL, 1 Rond Point Maurice Bellonte, telephone: (202) 267–8783. The Order is
31707 Blagnac Cedex, France; telephone: +33
postcard on which the following
also available for inspection at the
5 61 93 36 96; fax: +33 5 61 93 45 80; email:
statement is made: ‘‘Comments to
National Archives and Records
airworthiness.A330-A340@airbus.com; Docket No. FAA–2017–1088, Airspace
Administration (NARA). For
internet: http://www.airbus.com. You may Docket No. 17–AWP–25’’. The postcard
information on the availability of FAA
view this service information at the FAA, will be date/time stamped and returned
Order 7400.11B at NARA, call (202)
Transport Standards Branch, 2200 South to the commenter.
741–6030, or go to https://
216th St., Des Moines, WA. For information All communications received on or
www.archives.gov/federal-register/cfr/
on the availability of this material at the before the specified closing date for
ibr-locations.html.
FAA, call 206–231–3195. comments will be considered before
FAA Order 7400.11, Airspace
taking action on the proposed rule. The
Issued in Renton, Washington, on February Designations and Reporting Points, is
proposal contained in this notice may
14, 2018. published yearly and effective on
be changed in light of the comments
September 15.
daltland on DSKBBV9HB2PROD with PROPOSALS
Michael Kaszycki, received. A report summarizing each
Acting Director, System Oversight Division, FOR FURTHER INFORMATION CONTACT: Tom substantive public contact with FAA
Aircraft Certification Service. Clark, Federal Aviation Administration, personnel concerned with this
[FR Doc. 2018–03599 Filed 2–23–18; 8:45 am] Operations Support Group, Western rulemaking will be filed in the docket.
Service Center, 1601 Lind Avenue SW,
BILLING CODE 4910–13–P Availability of NPRMs
Renton, WA 98057; telephone (425)
203–4511. An electronic copy of this document
SUPPLEMENTARY INFORMATION: may be downloaded through the
VerDate Sep<11>2014 17:05 Feb 23, 2018 Jkt 244001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\26FEP1.SGM 26FEP1](https://thefederalregister.org/doc/83_FR_8239/page/7.svg)
Document Created: 2018-02-24 01:00:44
Document Modified: 2018-02-24 01:00:44
| 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 April 12, 2018. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229. | |
| FR Citation | 83 FR 8201 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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