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Timestamp: 2020-04-05 22:07:39
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Matched Legal Cases: ['art 39', 'art 39', 'art 51', 'art 39', 'art 39', 'ART 39', 'art 39', 'art 51']

[Docket No. FAA ; Product Identifier 2016-NM-200-AD; Amendment ; AD ] - PDF Free Download
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1 [Federal Register Volume 82, Number 232 (Tuesday, December 5, 2017)] [Rules and Regulations] [Pages ] From the Federal Register Online via the Government Publishing Office [ [FR Doc No: ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA ; Product Identifier 2016-NM-200-AD; Amendment ; AD ] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; and Model A , -212, -214, -216, -231, -232, and -233 airplanes. This AD was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. This AD requires repetitive inspections for cracking of the external bottom skin in certain areas on the left and right wings, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 9, The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 9, ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office EIAS, 1 Rond Point Maurice Bellonte, Blagnac Cedex, France; telephone ; fax ; Internet 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 It is also available on the Internet at by searching for and locating Docket No. FAA Examining the AD Docket You may examine the AD docket on the Internet at by searching for and locating Docket No. FAA ; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, 1
2 the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone ) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA ; telephone ; fax SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318 and A319 series airplanes; and Model A , - 212, -214, -216, -231, -232, and -233 airplanes. The NPRM published in the Federal Register on July 25, 2017 (82 FR 34453) ( the NPRM ). The NPRM was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. The NPRM proposed to require repetitive inspections for cracking of the external bottom skin in certain areas on the left and right wings, and corrective actions if necessary, and provided an optional terminating modification for the repetitive inspections. We are issuing this AD to detect and correct cracking of the external bottom skin in the area of the rib 2 attachment of the wings, which could result in reduced structural integrity of the wings. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD , dated November 7, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or the MCAI ), to correct an unsafe condition for certain Airbus Model A318 and A319 series airplanes; and Model A , - 212, -214, -216, -231, -232, and -233 airplanes. The MCAI states: During installation in production of new wing box ribs on post-mod aeroplanes, it was discovered that the centre wing lower rib foot angle was not matching with the bottom skin panel inner surface. This condition, if not detected and corrected, could induce fatigue cracking of the skin panel at the rib foot attachment, with possible detrimental effect on wing structural integrity. This condition was initially addressed by Airbus on the production line through adaptation mod , then through mod For affected aeroplanes in service, Airbus issued Service Bulletin (SB) A , providing instructions for repetitive detailed inspections (DET) or special detailed inspections (SDI), and SB A , providing modification instructions. For the reasons described above, this [EASA] AD requires repetitive inspections (DET or SDI) of the wing bottom skin lower surface for crack detection and, depending on findings, the accomplishment of applicable corrective action(s). This [EASA] AD also includes reference to an optional modification (Airbus SB A ), providing terminating action for the repetitive inspections required by this [EASA] AD. The corrective action for cracking is to repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; EASA; or Airbus's EASA Design 2
3 Organization Approval. You may examine the MCAI in the AD docket on the Internet at by searching for and locating Docket No. FAA Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response. Request To Include Technical Adaptations Delta Airlines asked for another Contacting the Manufacturer subparagraph acknowledging Technical Adaptations from Airbus to be added under paragraph (j) of the proposed AD, Other FAA AD Provisions. Delta observed that the FAA provision for contacting the manufacturer in paragraph (j) of the proposed AD would provide allowances for corrective actions without alternative methods of compliance (AMOCs). Delta noted that operators often receive Technical Adaptations that include an EASA Design Organization Approval (DOA) authorized signature for typographical, omitted instruction, and technical errors, and that they should be included in the proposed AD. We disagree with the commenter. The Contacting the Manufacturer paragraph in ADs only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. This paragraph states, in part, that for any requirement in an AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA; or the EASA; or Airbus's EASA DOA. We do not agree to extend this allowance to other AD requirements. All deviations from the service information sections that are marked RC (Required for Compliance) require AMOC approval unless otherwise stated in the AD. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A , dated May 26, This service information describes procedures for inspecting the external bottom skin for cracking in the area of the rib 2 attachment between stringer 8 and stringer 11 on both wings, and repairing any cracks. Airbus has also issued Service Bulletin A , including Appendix 01 and Appendix 02, dated May 26, This service information describes procedures for inspecting the lower rib feet (rib 2) and the bottom skin upper surface on both wings for cracking, modifying the wings by installing shims between the lower rib foot (rib 2) and the bottom skin upper surface, and repairing any cracks. 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. 3
4 Costs of Compliance We estimate that this AD affects 10 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs Action Labor cost Parts cost Inspection 5 work-hours $85 per hour = $425 per inspection cycle Cost per product $0 $425 per inspection cycle Cost on U.S. operators $4,250 per inspection cycle. Estimated Costs for Optional Actions Action Labor cost Parts cost Cost per product Modification 32 work-hours $85 per hour = $2,720 $5,750 $8,470 We have received no definitive data that would enable us to provide cost estimates for the oncondition actions specified in this AD. According to the manufacturer, some of the costs of the optional modification of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. 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 AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order C. 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 AD will not have federalism implications under Executive Order This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a significant regulatory action under Executive Order 12866; 2. Is not a significant rule under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 4
5 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39 AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, [Amended] 2. The FAA amends by adding the following new airworthiness directive (AD): 5
6 FAA Aviation Safety AIRWORTHINESS DIRECTIVE Airbus: Amendment ; Docket No. FAA ; Product Identifier NM-200-AD. (a) Effective Date This AD is effective January 9, (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers on which Airbus Modification was embodied in production, except those airplanes on which Airbus Modification or Modification was embodied in production. (1) Airbus Model A , -112, -121, and -122 airplanes. (2) Airbus Model A , -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A , -212, -214, -216, -231, -232, and -233 airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. Misalignment of the lower rib foot angle of the center wing box with the bottom skin panel inner surface could induce fatigue cracking of the skin panel at the rib foot attachment. We are issuing this AD to detect and correct cracking of the external bottom skin in the area of the rib 2 attachment of the wings, which could result in reduced structural integrity of the wings. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Before exceeding the applicable compliance time specified in table 1 to paragraph (g) of this AD, or within 3 months after the effective date of this AD, whichever occurs later: Do a detailed inspection or a special detailed inspection for cracking of the external bottom skin in the area of the rib 2 attachment between stringer 8 and stringer 11 of the left and right wings, and do all applicable 6
7 corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A , dated May 26, Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable intervals, based on the method used for the most recent inspection, as specified in table 2 to paragraph (g) of this AD. Table 1 to Paragraph (g) of This AD Initial Inspection Times Airplane model and configuration Model A318 series airplanes; Model A319 series airplanes; and Model A , -212, -214, -216, -231, -232, and -233 airplanes; pre-airbus Modification ; not used as VIP or Elite Model A318 series airplanes; Model A319 series airplanes; and Model A , -212, -214, -216, -231, -232, and -233 airplanes; post-airbus Modification ; not used as VIP or Elite Model A319 series airplanes; post-airbus Modifications 28162, 28238, and 28342; used as VIP or CJ Model A318 series airplanes; post-airbus Modification 39195; used as VIP or Elite Compliance time whichever occurs first since first flight of the airplane Before the accumulation of 14,500 total flight cycles or 29,000 total flight hours. Before the accumulation of 13,600 total flight cycles or 27,300 total flight hours. Before the accumulation of 7,400 total flight cycles or 32,000 total flight hours. Before the accumulation of 14,500 total flight cycles or 43,500 total flight hours. Table 2 to Paragraph (g) of This AD Repetitive Inspection Intervals Airplane model and configuration Model A318 series airplanes; Model A319 series airplanes; and Model A , -212, -214, -216, - 231, -232, and -233 airplanes; not used as VIP or Elite Model A319 series airplanes; post-airbus Modifications 28162, and 28342; used as VIP or CJ Model A318 series airplanes; post-airbus Modification 39195; used as VIP or Elite Detailed inspection whichever occurs first 4,000 flight cycles or 8,000 flight hours 2,000 flight cycles or 8,600 flight hours 4,000 flight cycles or 12,000 flight hours Special detailed inspection whichever occurs first 5,000 flight cycles or 10,000 flight hours. 2,500 flight cycles or 11,000 flight hours. 5,000 flight cycles or 15,000 flight hours. Note 1 to paragraph (g) of this AD: Airbus Modification defines the minimum airplane configuration for operation on Commonwealth of Independent States runway profiles. (h) Terminating Action Limitation Repair of an airplane, as required by paragraph (g) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD unless otherwise specified in the instructions obtained using the procedures specified in paragraph (j)(2) of this AD. 7
8 (i) Optional Terminating Action Modification of the wings including a detailed inspection of the lower rib feet (rib 2) and bottom skin upper surface of the wings for cracking and all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A , including Appendix 01 and Appendix 02, dated May 26, 2016, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane. If, during modification of an airplane as specified in this paragraph, accomplishment of any modification instruction is not possible due to configuration difficulties, accomplish the modification using the procedures specified in paragraph (j)(1) of this AD. (j) 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 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 Branch, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be ed to: 9-ANM-116-AMOC- 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: 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 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. (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. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD , dated November 7, 2016, for related information. This MCAI may be found in the AD docket on the Internet at by searching for and locating Docket No. FAA (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA ; telephone ; fax (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. 8
9 (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A , dated May 26, (ii) Airbus Service Bulletin A , including Appendix 01 and Appendix 02, dated May 26, (3) For service information identified in this AD, contact Airbus, Airworthiness Office EIAS, 1 Rond Point Maurice Bellonte, Blagnac Cedex, France; telephone ; fax ; Internet (4) 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 (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call , or go to: Issued in Renton, Washington, on November 22, Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. 9