Airworthiness Directives; Airbus Airplanes, 24690-24694 [2018-11421]

Download as PDF 24690 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules (a) Comments Due Date We must receive comments by July 16, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 747–8 and 747–8F series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 35, Oxygen. (e) Unsafe Condition This AD was prompted by a report that flightcrew oxygen masks did not function as designed during flight testing. We are issuing this AD to address flightcrew oxygen masks/ regulators that do not deploy correctly, which could result in a delay for the flightcrew to put on the masks, which may lead to hypoxia and loss of useful consciousness, potentially resulting in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions For airplanes with an original certificate of airworthiness, or an original export certificate of airworthiness, issued on or before the effective date of this AD: Within 72 months after the effective date of this AD, inspect for oxygen mask/regulator part number (P/N) MLD20–626–1 and stowage box P/N MXP806–1. If any oxygen mask/ regulator P/N MLD20–626–1 or stowage box P/N MXP806–1 is found, within 72 months after the effective date of this AD, do all applicable actions identified as ‘‘RC’’ (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–35–2133, Revision 1, dated November 1, 2017, except as provided by paragraph (h) of this AD. A review of airplane maintenance records is acceptable in lieu of the part number inspection if the part numbers of the oxygen mask/regulator and stowage box can be conclusively determined from that review. sradovich on DSK3GMQ082PROD with PROPOSALS (h) Exceptions to Service Information Specifications Where Boeing Special Attention Service Bulletin 747–35–2133, Revision 1, dated November 1, 2017, refers to or specifies installing a new (or changed) part, for this AD, a new or serviceable (or changed) part is acceptable. (i) Parts Installation Limitation (1) For airplanes with an original certificate of airworthiness, or an original export certificate of airworthiness, issued on or before the effective date of this AD: As of the effective date of this AD, no person may install an oxygen mask/regulator P/N MLD20–626–1 on any airplane, except that prior to 72 months after the effective date of this AD, installation of P/N MLD20–626–1 is VerDate Sep<11>2014 16:20 May 29, 2018 Jkt 244001 acceptable for unscheduled maintenance as a replacement only for another P/N MLD20– 626–1 and only into a stowage box P/N MXP806–1. If an oxygen mask/regulator having a part number other than P/N MLD20–626–1 is installed, it may not be replaced with P/N MLD20–626–1. For the purposes of this AD, unscheduled maintenance is defined as maintenance that was not planned for or scheduled in advance, such as changing a defective or unserviceable oxygen mask at dispatch. (2) For airplanes with an original certificate of airworthiness or an original export certificate of airworthiness issued after the effective date of this AD: As of the effective date of this AD, no person may install oxygen mask/regulator P/N MLD20–626–1, on any airplane. (3) For all airplanes: As of the effective date of this AD, no person may install oxygen mask/regulator P/N MLD20–726–1, in combination with any stowage box part number that is not P/N MXP806–7, on any airplane. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO 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 certification office, send it to the attention of the person identified in paragraph (k)(1) of this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (k) Related Information (1) For more information about this AD, contact Susan L. Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Seattle ACO Branch, 2200 South 216th Street, Des Moines, WA 98198; phone and fax: 206–231–3570; email: susan.l.monroe@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.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. Issued in Des Moines, Washington, on May 21, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–11426 Filed 5–29–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0455; Product Identifier 2017–NM–121–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 98–18–24, which applies to certain Airbus Model A320 series airplanes. AD 98–18–24 requires repetitive inspections to detect cracking in the inner flange of a certain door frame, and corrective actions, if necessary. AD 98–18–24 also provides an optional terminating action for the repetitive inspections. Since we issued AD 98–18–24, it has been determined that the compliance times for the repetitive inspections must be reduced. This proposed AD would continue to require the repetitive inspections of the inner flange of a certain door frame, with reduced repetitive inspection intervals, and corrective action if necessary. We are proposing this AD to address the unsafe condition on these products. SUMMARY: E:\FR\FM\30MYP1.SGM 30MYP1 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules We must receive comments on this proposed AD by July 16, 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, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. DATES: Examining the AD Docket sradovich on DSK3GMQ082PROD with PROPOSALS You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0455; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0455; Product Identifier 2017– NM–121–AD’’ at the beginning of your comments. We specifically invite VerDate Sep<11>2014 16:20 May 29, 2018 Jkt 244001 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 98–18–24, Amendment 39–10740 (63 FR 49272, September 15, 1998) (‘‘AD 98–18–24’’), for certain A320 series airplanes. AD 98–18–24 was prompted by the results of a fatigue test on simulated flights which revealed cracks on the inner flange of door frame 66 at stringers 18 and 20. The cracks were located in the gusset plate attachment holes and were hidden by the gusset plates. AD 98–18–24 requires repetitive inspections to detect cracking in the inner flange of door frame 66, and corrective actions if necessary. AD 98– 18–24 also provides an optional terminating action for the repetitive inspections. We issued AD 98–18–24 to detect and correct fatigue cracking in the inner flange of door frame 66, which could result in reduced structural integrity of the airplane. Since we issued AD 98–18–24, based on the results from a full scale fatigue test, it has been determined that the repetitive inspection intervals must be reduced. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017–0128, dated July 24, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A320–211 and A320–231 airplanes. The MCAI states: During fatigue test on simulated flights, cracks developed on the inner flange of door frame 66 at stringer 18 and 20 positions. These cracks were located in the gusset plate attachment holes and were hidden by the plates. This condition, if not detected and corrected, could affect the structural integrity of the fuselage. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 53–1071, later revised, to provide instructions to inspect and repair the gusset plate attachment holes at frame 66, at stringers 18, 20 and 22 both left hand (LH) and right hand (RH) side of the fuselage (hereafter collectively referred to as ‘‘the attachment holes’’ in this [EASA] AD), and PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 24691 [Airbus] SB A320–53–1072, providing instructions for reworking of the attachment holes. Consequently, DGAC France issued [French] AD 1996–234–087, later revised [which corresponds to FAA AD 98–18–24], requiring repetitive inspections and, depending on findings, repair of the attachment holes, and including reference to a reworking procedure, which constitutes optional terminating action for the repetitive inspections of the attachment holes. Since that [French] AD was issued, based on results from a full scale fatigue test, it was determined that the inspection intervals must be reduced. Airbus issued SB A320–53–1071 Revision 03, modifying the inspection threshold and intervals, and not changing the inspection instructions. For the reason described above, this [EASA] AD retains the requirement of DGAC France AD 1996–234–087 R1, which is superseded, and requires reduction of the repetitive inspection interval. 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– 0455. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–53–1071, Revision 03, dated July 20, 2017. This service information describes procedures for detailed inspections of the gusset plate attachment holes at door frame 66 for cracking and corrective action. Airbus also issued Service Bulletin A320–53–1072, Revision 02, dated May 5, 2016. This service information describes procedures for modification of the gusset frame attachment at door frame 66. 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. Costs of Compliance We estimate that this proposed AD affects 3 airplanes of U.S. registry. E:\FR\FM\30MYP1.SGM 30MYP1 24692 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules sradovich on DSK3GMQ082PROD with PROPOSALS The actions required by AD 98–18–24, 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 98–18–24 is $680 per product. We estimate that it would take about 19 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $4,845, or $1,615 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. In addition, we estimate that the optional terminating action would take about 20 work-hours per product, at an average labor rate of $85 per work-hour. Required parts costs would be about $60. Based on these figures, the estimated cost of the optional terminating action would be $1,760 per product. We also estimate that it would take about 1 work-hour per product to comply with the proposed reporting requirement in this proposed AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of reporting the inspection results on U.S. operators to be $255, or $85 per product. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. 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 VerDate Sep<11>2014 16:20 May 29, 2018 Jkt 244001 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 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: PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 98–18–24 Amendment 39–10740 (63 FR 49272, September 15, 1998), and adding the following new AD: ■ Airbus: Docket No. FAA–2018–0455; Product Identifier 2017–NM–121–AD. (a) Comments Due Date We must receive comments by July 16, 2018. (b) Affected ADs This AD replaces AD 98–18–24 Amendment 39–10740 (63 FR 49272, September 15, 1998) (‘‘AD 98–18–24’’). (c) Applicability This AD applies to Airbus Model A320– 211 and Model A320–231 airplanes, certificated in any category, serial numbers 0029, 0045, 0046, 0049 through 0057 inclusive, 0059, 0064, and 0065. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracks on the inner flange of door frame 66 at stringer 18 and 20 positions and by the results of a full scale fatigue test that indicated the intervals for the repetitive inspections required by AD 98–18–24 must be reduced. We are issuing this AD to detect and correct fatigue cracking in the inner flange of door frame 66, 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 Eddy Current Inspection, With No Changes This paragraph restates the requirements of paragraph (a) of AD 98–18–24, with no changes. For Model A320 series airplanes on which Airbus Modification 21778 (reference Airbus Service Bulletin A320–53–1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996) has not been accomplished: Prior to the accumulation of 20,000 total flight cycles, or within 1 year after October 20, 1998 (the effective date of AD 98–18–24), whichever occurs later: Perform a rotating probe eddy current inspection to detect cracking around the edges of the gusset plate attachment holes of the inner flange of door frame 66, left and right, at stringer positions P18, P20, and P22, in accordance with Airbus Service Bulletin A320–53–1071, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, E:\FR\FM\30MYP1.SGM 30MYP1 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules (h) Retained Optional Terminating Action, With No Changes This paragraph restates the optional terminating action of paragraph (b) of AD 98– 18–24, with no changes. Modification of the gusset plate attachment holes of the inner sradovich on DSK3GMQ082PROD with PROPOSALS (j) Corrective Actions (1) If, during any inspection required by paragraph (i) of this AD, any crack is found on a gusset plate attachment hole: Before further flight, repair the affected attachment hole, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1071, Revision 03, dated July 20, 2017, except as required by paragraph (n) of this AD. (2) If, during any inspection required by paragraph (i) of this AD, any crack is found on any other hole of the gusset plate: Before further flight, contact the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA); for approved repair instructions and accomplish those instructions accordingly. If approved VerDate Sep<11>2014 16:20 May 29, 2018 Jkt 244001 flange of door frame 66, left and right (Airbus Modification 21778), in accordance with Airbus Service Bulletin A320–53–1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996, constitutes terminating action for the repetitive inspection requirements of paragraph (g) of this AD. (i) New Requirement of This AD: Repetitive Inspections At the applicable compliance time specified in figure 1 to paragraph (i) of this AD, do a rotating probe eddy current inspection to detect cracking around the edges of the gusset plate attachment holes of the inner flange of door frame 66, left and right, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1071, Revision 03, dated July 20, 2017. Repeat the inspection thereafter at intervals not to exceed 10,900 flight cycles. by the DOA, the approval must include the DOA-authorized signature. terminates the inspections required by paragraph (g) of this AD. (k) Terminating Action for This AD (l) Optional Modification (1) Repair of an attachment hole area as required by paragraph (j)(1) of this AD terminates the repetitive inspections required by paragraph (i) of this AD for that attachment hole area on that airplane only. (2) Repair of any other hole of the gusset plate, as required by paragraph (j)(2) of this AD, does not terminate the repetitive inspections required by paragraph (i) of this AD for that airplane, unless specified otherwise in the repair instructions provided by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus’s EASA DOA. (3) Accomplishing the initial inspection required by paragraph (i) of this AD Modification of the gusset plate attachment holes of the inner flange of door frame 66, left and right, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1072, Revision 02, dated May 5, 2016, terminates the repetitive inspections required by paragraph (i) of this AD for that airplane. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 (m) Reporting Report the results of the inspection required by paragraph (i) of this AD that are done on or after the effective date of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https:// w3.airbus.com/), or submit the results to Airbus in accordance with the instructions of E:\FR\FM\30MYP1.SGM 30MYP1 EP30MY18.000</GPH> 1996. If any crack is detected, prior to further flight, repair in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA. Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles. 24693 24694 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules Airbus Service Bulletin A320–53–1071, Revision 03, dated July 20, 2017. Submit the report within 30 days after accomplishing the inspection required by paragraph (i) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. If operators have reported findings as part of obtaining any corrective actions approved by the EASA DOA, operators are not required to report those findings as specified in this paragraph. (n) Service Information Exception Where Airbus Service Bulletin A320–53– 1071, Revision 03, dated July 20, 2017, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (q)(2) of this AD. (o) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1071, Revision 01, dated July 4, 2002; or Airbus Service Bulletin A320–53–1071, Revision 02, dated May 5, 2016. (2) This paragraph provides credit for actions identified in paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996; or Airbus Service Bulletin A320–53–1072, Revision 01, dated July 4, 2002. sradovich on DSK3GMQ082PROD with PROPOSALS (p) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (q) 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 VerDate Sep<11>2014 16:20 May 29, 2018 Jkt 244001 Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (r)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (ii) AMOCs approved previously for AD 98–18–24 are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraph (n) 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0128, dated July 24, 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–2018–0455. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet http://www.airbus.com. You may view this 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 Des Moines, Washington, on May 21, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–11421 Filed 5–29–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0453; Product Identifier 2018–NM–028–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC–8–400 series airplanes. This proposed AD was prompted by reports of the nose landing gear (NLG) locking in a partially extended position due to loose bushings on the lock link of the NLG locking mechanism. This proposed AD would require inspecting the bushings and the lower lock link of the NLG for discrepancies, and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by July 16, 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 Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone: 416–375–4000; fax: 416–375–4539; email: thd.qseries@ aero.bombardier.com; internet: http:// www.bombardier.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. DATES: Examining the AD Docket You may examine the AD docket on the internet at http:// E:\FR\FM\30MYP1.SGM 30MYP1

Agencies

[Federal Register Volume 83, Number 104 (Wednesday, May 30, 2018)]
[Proposed Rules]
[Pages 24690-24694]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11421]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-18-24, 
which applies to certain Airbus Model A320 series airplanes. AD 98-18-
24 requires repetitive inspections to detect cracking in the inner 
flange of a certain door frame, and corrective actions, if necessary. 
AD 98-18-24 also provides an optional terminating action for the 
repetitive inspections. Since we issued AD 98-18-24, it has been 
determined that the compliance times for the repetitive inspections 
must be reduced. This proposed AD would continue to require the 
repetitive inspections of the inner flange of a certain door frame, 
with reduced repetitive inspection intervals, and corrective action if 
necessary. We are proposing this AD to address the unsafe condition on 
these products.

[[Page 24691]]


DATES: We must receive comments on this proposed AD by July 16, 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, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; 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-
0455; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA; 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0455; 
Product Identifier 2017-NM-121-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 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 98-18-24, Amendment 39-10740 (63 FR 49272, September 
15, 1998) (``AD 98-18-24''), for certain A320 series airplanes. AD 98-
18-24 was prompted by the results of a fatigue test on simulated 
flights which revealed cracks on the inner flange of door frame 66 at 
stringers 18 and 20. The cracks were located in the gusset plate 
attachment holes and were hidden by the gusset plates. AD 98-18-24 
requires repetitive inspections to detect cracking in the inner flange 
of door frame 66, and corrective actions if necessary. AD 98-18-24 also 
provides an optional terminating action for the repetitive inspections. 
We issued AD 98-18-24 to detect and correct fatigue cracking in the 
inner flange of door frame 66, which could result in reduced structural 
integrity of the airplane.
    Since we issued AD 98-18-24, based on the results from a full scale 
fatigue test, it has been determined that the repetitive inspection 
intervals must be reduced.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0128, dated July 24, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A320-211 and A320-231 airplanes. The MCAI states:

    During fatigue test on simulated flights, cracks developed on 
the inner flange of door frame 66 at stringer 18 and 20 positions. 
These cracks were located in the gusset plate attachment holes and 
were hidden by the plates.
    This condition, if not detected and corrected, could affect the 
structural integrity of the fuselage.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1071, later revised, to provide 
instructions to inspect and repair the gusset plate attachment holes 
at frame 66, at stringers 18, 20 and 22 both left hand (LH) and 
right hand (RH) side of the fuselage (hereafter collectively 
referred to as ``the attachment holes'' in this [EASA] AD), and 
[Airbus] SB A320-53-1072, providing instructions for reworking of 
the attachment holes.
    Consequently, DGAC France issued [French] AD 1996-234-087, later 
revised [which corresponds to FAA AD 98-18-24], requiring repetitive 
inspections and, depending on findings, repair of the attachment 
holes, and including reference to a reworking procedure, which 
constitutes optional terminating action for the repetitive 
inspections of the attachment holes.
    Since that [French] AD was issued, based on results from a full 
scale fatigue test, it was determined that the inspection intervals 
must be reduced. Airbus issued SB A320-53-1071 Revision 03, 
modifying the inspection threshold and intervals, and not changing 
the inspection instructions.
    For the reason described above, this [EASA] AD retains the 
requirement of DGAC France AD 1996-234-087 R1, which is superseded, 
and requires reduction of the repetitive inspection interval.

    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-
0455.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1071, Revision 03, dated 
July 20, 2017. This service information describes procedures for 
detailed inspections of the gusset plate attachment holes at door frame 
66 for cracking and corrective action.
    Airbus also issued Service Bulletin A320-53-1072, Revision 02, 
dated May 5, 2016. This service information describes procedures for 
modification of the gusset frame attachment at door frame 66.
    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.

Costs of Compliance

    We estimate that this proposed AD affects 3 airplanes of U.S. 
registry.

[[Page 24692]]

    The actions required by AD 98-18-24, 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 98-18-24 is $680 per product.
    We estimate that it would take about 19 work-hours per product to 
comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $4,845, or $1,615 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    In addition, we estimate that the optional terminating action would 
take about 20 work-hours per product, at an average labor rate of $85 
per work-hour. Required parts costs would be about $60. Based on these 
figures, the estimated cost of the optional terminating action would be 
$1,760 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the proposed reporting requirement in this proposed AD. 
The average labor rate is $85 per hour. Based on these figures, we 
estimate the cost of reporting the inspection results on U.S. operators 
to be $255, or $85 per product.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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 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) 
98-18-24 Amendment 39-10740 (63 FR 49272, September 15, 1998), and 
adding the following new AD:

Airbus: Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD.

(a) Comments Due Date

    We must receive comments by July 16, 2018.

(b) Affected ADs

    This AD replaces AD 98-18-24 Amendment 39-10740 (63 FR 49272, 
September 15, 1998) (``AD 98-18-24'').

(c) Applicability

    This AD applies to Airbus Model A320-211 and Model A320-231 
airplanes, certificated in any category, serial numbers 0029, 0045, 
0046, 0049 through 0057 inclusive, 0059, 0064, and 0065.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracks on the inner flange 
of door frame 66 at stringer 18 and 20 positions and by the results 
of a full scale fatigue test that indicated the intervals for the 
repetitive inspections required by AD 98-18-24 must be reduced. We 
are issuing this AD to detect and correct fatigue cracking in the 
inner flange of door frame 66, 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 Eddy Current Inspection, With No Changes

    This paragraph restates the requirements of paragraph (a) of AD 
98-18-24, with no changes. For Model A320 series airplanes on which 
Airbus Modification 21778 (reference Airbus Service Bulletin A320-
53-1072, dated November 7, 1995, as revised by Change Notice 0A, 
dated July 5, 1996) has not been accomplished: Prior to the 
accumulation of 20,000 total flight cycles, or within 1 year after 
October 20, 1998 (the effective date of AD 98-18-24), whichever 
occurs later: Perform a rotating probe eddy current inspection to 
detect cracking around the edges of the gusset plate attachment 
holes of the inner flange of door frame 66, left and right, at 
stringer positions P18, P20, and P22, in accordance with Airbus 
Service Bulletin A320-53-1071, dated November 7, 1995, as revised by 
Change Notice 0A, dated July 5,

[[Page 24693]]

1996. If any crack is detected, prior to further flight, repair in 
accordance with a method approved by the Manager, International 
Section, Transport Standards Branch, FAA. Repeat the inspection 
thereafter at intervals not to exceed 20,000 flight cycles.

(h) Retained Optional Terminating Action, With No Changes

    This paragraph restates the optional terminating action of 
paragraph (b) of AD 98-18-24, with no changes. Modification of the 
gusset plate attachment holes of the inner flange of door frame 66, 
left and right (Airbus Modification 21778), in accordance with 
Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as 
revised by Change Notice 0A, dated July 5, 1996, constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (g) of this AD.

(i) New Requirement of This AD: Repetitive Inspections

    At the applicable compliance time specified in figure 1 to 
paragraph (i) of this AD, do a rotating probe eddy current 
inspection to detect cracking around the edges of the gusset plate 
attachment holes of the inner flange of door frame 66, left and 
right, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. 
Repeat the inspection thereafter at intervals not to exceed 10,900 
flight cycles.
[GRAPHIC] [TIFF OMITTED] TP30MY18.000

(j) Corrective Actions

    (1) If, during any inspection required by paragraph (i) of this 
AD, any crack is found on a gusset plate attachment hole: Before 
further flight, repair the affected attachment hole, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1071, Revision 03, dated July 20, 2017, except as required 
by paragraph (n) of this AD.
    (2) If, during any inspection required by paragraph (i) of this 
AD, any crack is found on any other hole of the gusset plate: Before 
further flight, contact the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); 
for approved repair instructions and accomplish those instructions 
accordingly. If approved by the DOA, the approval must include the 
DOA-authorized signature.

(k) Terminating Action for This AD

    (1) Repair of an attachment hole area as required by paragraph 
(j)(1) of this AD terminates the repetitive inspections required by 
paragraph (i) of this AD for that attachment hole area on that 
airplane only.
    (2) Repair of any other hole of the gusset plate, as required by 
paragraph (j)(2) of this AD, does not terminate the repetitive 
inspections required by paragraph (i) of this AD for that airplane, 
unless specified otherwise in the repair instructions provided by 
the Manager, International Section, Transport Standards Branch, FAA; 
or the EASA; or Airbus's EASA DOA.
    (3) Accomplishing the initial inspection required by paragraph 
(i) of this AD terminates the inspections required by paragraph (g) 
of this AD.

(l) Optional Modification

    Modification of the gusset plate attachment holes of the inner 
flange of door frame 66, left and right, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1072, 
Revision 02, dated May 5, 2016, terminates the repetitive 
inspections required by paragraph (i) of this AD for that airplane.

(m) Reporting

    Report the results of the inspection required by paragraph (i) 
of this AD that are done on or after the effective date of this AD 
to Airbus Service Bulletin Reporting Online Application on Airbus 
World (https://w3.airbus.com/), or submit the results to Airbus in 
accordance with the instructions of

[[Page 24694]]

Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 
2017. Submit the report within 30 days after accomplishing the 
inspection required by paragraph (i) of this AD. The report must 
include the inspection results, a description of any discrepancies 
found, the airplane serial number, and the number of landings and 
flight hours on the airplane. If operators have reported findings as 
part of obtaining any corrective actions approved by the EASA DOA, 
operators are not required to report those findings as specified in 
this paragraph.

(n) Service Information Exception

    Where Airbus Service Bulletin A320-53-1071, Revision 03, dated 
July 20, 2017, specifies to contact Airbus for appropriate action, 
and specifies that action as ``RC'' (Required for Compliance): 
Before further flight, accomplish corrective actions in accordance 
with the procedures specified in paragraph (q)(2) of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1071, Revision 01, dated July 4, 2002; or Airbus Service Bulletin 
A320-53-1071, Revision 02, dated May 5, 2016.
    (2) This paragraph provides credit for actions identified in 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1072, dated November 7, 1995, as revised by Change Notice 0A, dated 
July 5, 1996; or Airbus Service Bulletin A320-53-1072, Revision 01, 
dated July 4, 2002.

(p) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 1 hour per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(q) 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 Section, send it to the attention of 
the person identified in paragraph (r)(2) of this AD. Information 
may be emailed to: [email protected]ov.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOCs approved previously for AD 98-18-24 are approved as 
AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the 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 
paragraph (n) 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.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0128, dated July 24, 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-2018-0455.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; 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 Des Moines, Washington, on May 21, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-11421 Filed 5-29-18; 8:45 am]
BILLING CODE 4910-13-P