83 FR 44516 - Airworthiness Directives; Airbus SAS Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 170 (August 31, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 170 (August 31, 2018)
| Page Range | 44516-44521 | |
| FR Document | 2018-18813 |
[Federal Register Volume 83, Number 170 (Friday, August 31, 2018)] [Proposed Rules] [Pages 44516-44521] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-18813] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0762; Product Identifier 2018-NM-033-AD] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-07- 23, which applies to all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2016-07-23 requires, for certain airplanes, repetitive replacements of the fixed fairing upper and lower attachment studs of both the left-hand (LH) and right-hand (RH) main landing gear (MLG); and repetitive inspections for corrosion, wear, fatigue cracking, and loose studs of each forward stud assembly of the fixed fairing door upper and lower forward attachments of both the LH and RH MLG; and replacement if necessary. AD 2016-07-23 also provides an optional terminating modification for the repetitive replacements of the fixed fairing upper and lower attachment studs. Since we issued AD 2016-07-23, we have determined that for some airplane configurations, associated fixed fairing assembly part numbers susceptible to fatigue cracking were not listed in certain service information required by AD 2016-07-23. In addition, we have determined that additional work is necessary to re-identify the fixed fairing assembly part number on certain airplanes. This proposed AD would retain the requirements of AD 2016-07-23 and, for certain airplanes, require re-identification of the LH and RH fixed fairing assemblies' part numbers. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by October 15, 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--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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., [[Page 44517]] 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- 0762; 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 NPRM, 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-2018-0762; Product Identifier 2018-NM-033-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 2016-07-23, Amendment 39-18468 (81 FR 26115, May 2, 2016) (``AD 2016-07-23''), for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2016-07-23 requires, for certain airplanes, repetitive replacements of the fixed fairing upper and lower attachment studs of both the LH and RH MLG; and repetitive inspections for corrosion, wear, fatigue cracking, and loose studs of each forward stud assembly of the fixed fairing door upper and lower forward attachment of both the LH and RH MLG; and replacement if necessary. AD 2016-07-23 also provides an optional terminating modification for the repetitive replacements of the fixed fairing upper and lower attachment studs. AD 2016-07-23 resulted from reports of in-flight loss of fixed and hinged MLG fairings, and reports of post-modification MLG fixed fairing assemblies that have wear and corrosion. We issued AD 2016-07- 23 to address in-flight detachment of an MLG fixed fairing and consequent damage to the airplane. Actions Since AD 2016-07-23 Was Issued Since we issued AD 2016-07-23, we have determined that for some airplane configurations, associated fixed fairing assembly part numbers susceptible to fatigue cracking were not listed in certain service information required by AD 2016-07-23. In addition, we have determined that additional work is necessary to re-identify the fixed fairing assembly part number after completion of the optional terminating modification. This proposed AD would retain the requirements of AD 2016-07-23 and require re-identification of the part number of the LH and RH fixed fairing assemblies after completion of the optional terminating modification. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018-0023, dated January 26, 2018; corrected February 5, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus SAS Model A318 and A319 series airplanes; all Airbus SAS Model A320-211, A320- 212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and all Airbus SAS Model A321-111, A321-112, A321-131, A321-211, A321- 212, A321-213, A321-231 and A321-232 airplanes. The MCAI states: Several occurrences were reported of in-flight loss of main landing gear (MLG) fixed and hinged fairings. The majority of reported events occurred following scheduled maintenance activities. One result of the investigation was that a discrepancy between the drawing and the maintenance manuals was discovered. The maintenance documents were corrected to prevent mis-rigging of the MLG fixed and hinged fairings, which could induce fatigue cracking. Prompted by these findings, Airbus issued Service Bulletin (SB) A320-52-1083, providing instructions for a one-time inspection of the MLG fixed fairing composite insert and the surrounding area, replacement of the adjustment studs at the lower forward position and adjustment to the new clearance tolerances. That SB was replaced by Airbus SB A320-52-1100 (modification (mod) 27716) introducing a re-designed location stud, rod end and location plate at the forward upper and lower leg fixed-fairing positions. Subsequently, reports were received of post-mod 27716/post-SB A320-52-1100 MLG fixed fairing assemblies with corrosion, which could also induce cracking. This condition, if not detected and corrected, could lead to further cases of in-flight detachment of a MLG fixed fairing, possibly resulting in injury to persons on the ground and/or damage to the aeroplane. To address this potential unsafe condition, EASA issued AD 2014- 0096 to require repetitive detailed inspections (DET) of the MLG fixed fairings, and, depending on findings, accomplishment of applicable corrective actions. That [EASA] AD also prohibited installation of certain MLG fixed fairing rod end assemblies and studs as replacement parts on aeroplanes incorporating Airbus mod 27716 in production, or modified in accordance with Airbus SB A320- 52-1100 (any revision) in service. Since EASA AD 2014-0096 was issued, Airbus developed an alternative inspection programme to meet the [EASA] AD requirements. In addition, a terminating action (mod 155648) was developed, which was made available for in-service aeroplanes through Airbus SB A320- 52-1165. Consequently, EASA issued AD 2015-0001 (later revised), retaining the requirements of EASA AD 2014-0096, which was superseded, and adding an optional terminating action for the repetitive inspections. For post-mod aeroplanes, i.e. incorporating Airbus mod 155648 in production, or modified by Airbus SB A320-52- 1165 in service, the only remaining requirement was to ensure that pre-mod components are no longer installed. Since EASA AD 2015-0001R1 [which corresponds to FAA AD 2016-07- 23] was issued, Airbus revised SB A320-52-1165 to include additional work, to re-identify the fairing assembly part number (P/N). During the preparation of this additional work, it was noted that several configurations and associated P/N were not listed in the original SB, which may have an impact on aeroplanes on which SB A320-52-1165 original issue or Revision (rev.) 01 was already accomplished. It has also been noticed that the instructions for reidentification of two P/N were not correct in revision 02 of this SB. For the reasons described above, this [EASA] AD retains the requirement of EASA AD 2015-0001R1, which is superseded, but requires using the SB at rev. 03. This [EASA] AD also requires accomplishment of additional work [re-identification of the part number for the LH and RH fixed fairing assemblies] for those aeroplanes on which parts were replaced in accordance with the instructions of Airbus SB A320-52- 1165 at original issue, rev. 01 or rev. 02 and correct (re)identification as applicable. 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- 0762. [[Page 44518]] Related Service Information Under 1 CFR Part 51 Airbus SAS has issued the following service information. Airbus Service Bulletin A320-52-1100, Revision 01, dated March 12, 1999. This service information describes procedures for modification of the airplane to post-Airbus Modification 27716 configuration (by replacing the location stud, rod end, and location plate at the forward upper and lower leg fixed-fairing positions of the MLG door assemblies). The modification includes a resonance frequency inspection for debonding of the composite insert and delamination of the honeycomb area around the insert, and applicable corrective actions. Corrective actions include repairing the insert. The actions in this service information are an optional terminating modification. Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015. This service information describes procedures for inspection of the fixed fairing door upper and lower forward attachments of the LH and RH MLG, and replacement of the fixed fairing upper and lower attachment studs of the LH and RH MLG. Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017. The service information describes procedures for replacing the fixed fairing attachment stud assemblies of the MLG door assembly with new assemblies, and re-identifying the part number of the LH and RH MLG fixed fairing assemblies. The actions in this service information are an optional terminating modification. The 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 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. Proposed Requirements of This NPRM This proposed AD would retain all of the requirements of AD 2016- 07-23. This proposed AD would require accomplishing the actions specified in the service information described previously. Costs of Compliance We estimate that this proposed AD affects 901 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- 18 work-hours x $85 per hour = $1,530........................ $4,110 $5,640 $5,081,640 ---------------------------------------------------------------------------------------------------------------- Estimated Costs for Optional Actions ------------------------------------------------------------------------ Labor cost Parts cost Cost per product ------------------------------------------------------------------------ Up to 18 work-hours x $85 per Up to $4,110...... Up to $5,640 hour = $1,530. ------------------------------------------------------------------------ We estimate the following costs to do any necessary replacements or re-identifications that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements or re-identifications: On-Condition Costs ------------------------------------------------------------------------ Labor cost Parts cost Cost per product ------------------------------------------------------------------------ Up to 20 work-hours x $85 per Up to $4,110...... Up to $5,810 hour = $1,700. ------------------------------------------------------------------------ According to the manufacturer, some or all of the costs 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 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 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. [[Page 44519]] 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) 2016-07-23, Amendment 39-18468 (81 FR 26115, May 2, 2016), and adding the following new AD: Airbus SAS: Docket No. FAA-2018-0762; Product Identifier 2018-NM- 033-AD. (a) Comments Due Date We must receive comments by October 15, 2018. (b) Affected ADs This AD replaces AD 2016-07-23, Amendment 39-18468 (81 FR 26115, May 2, 2016) (``AD 2016-07-23''). (c) Applicability This AD applies to the Airbus SAS airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A318-111, A318-112, A318-121, and A318-122 airplanes. (2) Model A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, and A319-133 airplanes. (3) Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes. (4) Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231 and A321-232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by reports of in-flight loss of fixed and hinged main landing gear (MLG) fairings, and reports of post- modification MLG fixed fairing assemblies that have wear and corrosion. This AD was also prompted by a determination that for some airplane configurations, associated fixed fairing assembly part numbers susceptible to fatigue cracking were not listed in certain service information required by AD 2016-07-23. In addition, we have determined that additional work is necessary to re-identify the fixed fairing assembly part number on certain airplanes. We are issuing this AD to prevent in-flight detachment of an MLG fixed fairing and consequent damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Replacements, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2016-07-23, with no changes. For airplanes in pre-Airbus Modification 27716 and pre-Airbus Service Bulletin A320-52-1100 configuration, with any of the components installed that are identified in paragraphs (g)(1) through (g)(5) of this AD: At the applicable compliance time specified in paragraph (h) of this AD, replace fixed fairing upper and lower attachment studs of both left- hand (LH) and right-hand (RH) MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015. Repeat the replacements thereafter at intervals not to exceed 6,500 flight cycles. (1) Plate--support having part number (P/N) D5284024820000. (2) Plate--support having P/N D5284024820200. (3) Stud--adjustment having P/N D5284024420000. (4) Rod end assembly (lower) having P/N D5284000500000. (5) Rod end assembly (upper) having P/N D5284000600000. (h) Retained Compliance Times for the Requirements of Paragraph (g) of This AD, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2016-07-23, with no changes. For airplanes identified in paragraph (g) of this AD, except as provided by paragraph (o) of this AD: Do the initial replacement required by paragraph (g) of this AD at the latest of the times specified in paragraphs (h)(1) through (h)(4) of this AD. (1) Before the accumulation of 6,500 total flight cycles since the airplane's first flight. (2) Within 6,500 flight cycles since the last installation of a pre-Airbus Modification 27716 stud on the airplane. (3) Within 1,500 flight cycles after June 6, 2016 (the effective date of AD 2016-07-23). (4) Within 8 months after June 6, 2016 (the effective date of AD 2016-07-23). (i) Retained Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2016-07-23, with no changes. For airplanes in post-Airbus Modification 27716 or post-Airbus Service Bulletin A320-52-1100 configuration, with any of the components installed that are identified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD: At the applicable compliance time specified in paragraph (j) of this AD, do a detailed inspection of the LH and RH MLG forward stud assemblies of the fixed fairing door upper and lower forward attachments of both LH and RH MLG for indications of corrosion, wear, fatigue cracking, and loose studs, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015. Repeat the detailed inspection thereafter at intervals not to exceed 12 months. Replacement of both LH and RH MLG forward stud assemblies on an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015, extends the interval for the next detailed inspection to 72 months; and the inspection must be repeated thereafter at intervals not to exceed 12 months. (1) Stud--adjustment having P/N D5285600720000. (2) Rod end assembly (lower) having P/N D5285600400000. (3) Rod end assembly (upper) having P/N D5285600500000. (j) Retained Compliance Times for the Requirements of Paragraph (i) of This AD, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2016-07-23, with no changes. For airplanes identified in paragraph (i) of this AD, except as provided by paragraph (o) of this AD: Do the initial inspection required by paragraph (i) of this AD at the latest of the times specified in paragraphs (j)(1) through (j)(4) of this AD. (1) Before the accumulation of 72 months since the airplane's first flight. (2) Within 72 months since the last installation of a post- Airbus Modification 27716 assembly or since accomplishment of the actions specified in Airbus Service Bulletin A320-52-1100. (3) Within 1,500 flight cycles after June 6, 2016 (the effective date of AD 2016-07-23). (4) Within 8 months after June 6, 2016 (the effective date of AD 2016-07-23). [[Page 44520]] (k) Retained Corrective Action, With Revised Service Information This paragraph restates the requirements of paragraph (k) of AD 2016-07-23, with revised service information. If any discrepancy (including any indication of corrosion, wear, fatigue cracking, or loose studs) of any MLG forward stud assembly is found during any inspection required by paragraph (i) of this AD, except as specified in paragraph (l) of this AD: Before further flight, replace the discrepant upper and lower fixed fairing forward stud assemblies of the LH and RH MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017. As of the effective date of this AD only Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used. (l) Retained Corrective Action or Repetitive Inspections for Certain Corrosion Findings, With Revised Service Information This paragraph restates the requirements of paragraph (l) of AD 2016-07-23, with revised service information. If any corrosion is found during any inspection required by paragraph (i) of this AD on any MLG fixed fairing forward stud assembly (upper, lower, LH or RH), but the corroded stud is not loose: Do the action specified in paragraph (l)(1) or (l)(2) of this AD. (1) Before further flight, replace the affected assembly, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017. As of the effective date of this AD only Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used. (2) Within 4 months after finding corrosion, and thereafter at intervals not to exceed 4 months, do a detailed inspection for indications of corrosion, wear, fatigue cracking, and loose studs of the forward stud assembly of the affected (LH or RH) MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015. (m) Retained Corrective Action for Inspections Specified in Paragraph (l)(2) of This AD, With Revised Service Information This paragraph restates the requirements of paragraph (m) of AD 2016-07-23, with revised service information. If any indication of wear, fatigue cracking, or loose studs of any forward stud assembly is found during any inspection required by paragraph (l)(2) of this AD: Before further flight, replace the affected (LH or RH) MLG fixed fairing forward stud assembly, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017. As of the effective date of this AD only Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used. (n) Retained Terminating Action, With Revised Service Information This paragraph restates the requirements of paragraph (n) of AD 2016-07-23, with revised service information. (1) Replacement of parts on an airplane, as required by paragraph (g), (k), (l)(1), or (m) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (i) of this AD, except as specified in paragraph (n)(3) of this AD. (2) The repetitive replacements required by paragraph (g) of this AD may be terminated by modification of the airplane to post- Airbus Modification 27716 configuration, including a resonance frequency inspection for debonding of the composite insert and delamination of the honeycomb area around the insert, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1100, Revision 01, dated March 12, 1999, provided all applicable corrective actions are done before further flight. Thereafter, refer to paragraph (i) of this AD to determine the compliance time for the next detailed inspection required by this AD. (3) Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, constitutes terminating action for actions required by paragraphs (g) through (m) of this AD for the airplane on which the modification is done. As of the effective date of this AD only Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used. (o) Retained Exceptions to Certain AD Actions, With No Changes This paragraph restates the requirements of paragraph (o) of AD 2016-07-23, with no changes. An airplane on which Airbus Modification 155648 has been embodied in production is not affected by the requirements of paragraphs (g) and (i) of this AD, provided that no affected component, identified by part number as specified in paragraphs (g)(1) through (g)(5) and (i)(1) through (i)(3) of this AD, has been installed on that airplane since first flight of the airplane. (p) Retained Parts Installation Prohibition, With No Changes This paragraph restates the requirements of paragraph (p) of AD 2016-07-23, with no changes. (1) For airplanes in pre-Airbus Modification 27716 or pre-Airbus Service Bulletin A320-52-1100 configuration: No person may install a component identified in paragraphs (g)(1) through (g)(5) of this AD on any airplane after doing the actions provided in paragraph (n)(2) of this AD. (2) For airplanes in post-Airbus Modification 27716 or post Airbus Service Bulletin A320-52-1100 configuration: As of the effective date of this AD, no person may install a component identified in paragraphs (g)(1) through (g)(5) of this AD on any airplane. (3) For airplanes in pre-Airbus Modification 155648 or pre- Airbus Service Bulletin A320-52-1165 configuration: No person may install a component identified in paragraphs (g)(1) through (g)(5) and (i)(1) through (i)(3) of this AD on any airplane after doing the actions provided in paragraph (n)(3) of this AD. (4) For airplanes in post-Airbus Modification 155648 or post- Airbus Service Bulletin A320-52-1165 configuration: As of the effective date of this AD, no person may install a component identified in (g)(1) through (g)(5) and (i)(1) through (i)(3) of this AD on any airplane. (q) Retained No Reporting Requirement, With No Changes This paragraph restates the requirements of paragraph (q) of AD 2016-07-23, with no changes. Although Airbus Service Bulletin A320- 52-1163, Revision 01, including Appendix 01, dated June 22, 2015, specifies to submit certain information to the manufacturer, and specifies that action as ``RC'' (Required for Compliance), this AD does not include that requirement. (r) New Requirement of This AD: Additional Work For any airplane on which, before the effective date of this AD, any part was installed or replaced, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, dated November 3, 2014; Revision 01, dated October 13, 2015; or Revision 02, dated February 12, 2016: Within 12 months after the effective date of this AD, accomplish the instructions identified as ``additional work'' in the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, [[Page 44521]] Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, as applicable to the airplane configuration. (s) New Terminating Action Modification of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, or as specified in paragraph (r) of this AD constitutes terminating action for the requirements of paragraphs (g), (i), (k), (l), and (m) of this AD for that airplane. (t) New Parts Installation Prohibition (1) Do not install on any airplane a component specified in paragraphs (g)(1) through (g)(5) of this AD, as required by paragraph (t)(1)(i) or (t)(1)(ii) of this AD, as applicable. (i) For airplanes in pre-Airbus Modification 27716 or pre-Airbus Service Bulletin A320-52-1100 configuration: After completing the optional modification specified in paragraph (n)(2) of this AD. (ii) For airplanes in post-Airbus Modification 27716 or post Airbus Service Bulletin A320-52-1100 configuration: As of the effective date of this AD. (2) Do not install on any airplane a component specified in paragraphs (g)(1) through (g)(5) of this AD or paragraphs (i)(1) through (i)(3) of this AD, as required by paragraph (t)(2)(i) or (t)(2)(ii) of this AD, as applicable. (i) For airplanes in pre-Airbus Modification 155648 or pre- Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, configuration: After completion of the additional work required by paragraph (r) of this AD. (ii) For airplanes in post-Airbus Modification 155648 or post- Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, configuration: As of the effective date of this AD. (u) Credit for Previous Actions (1) This paragraph provides credit for optional actions provided by paragraph (n)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1100, dated December 7, 1998. (2) This paragraph provides credit for the actions required by paragraphs (g), (i), (k), (l), and (m) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1163, dated February 4, 2014. (3) This paragraph provides credit for the actions required by paragraphs (k), (l)(1), (m), and (n)(3) of this AD if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015. (v) 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 (w)(2) of this AD. Information may be emailed to: [email protected]. (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 2016-07-23 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 European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as specified by paragraph (q) 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. (w) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018-0023, dated January 26, 2018; corrected February 5, 2018; 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-2018-0762. (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 SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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 August 17, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-18813 Filed 8-30-18; 8:45 am] BILLING CODE 4910-13-P
![44516 Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Proposed Rules
(g) Definitions for This AD directly to the International Branch, send it SUMMARY: We propose to supersede
(1) An affected part is a RAT hydraulic to the attention of the person identified in Airworthiness Directive (AD) 2016–07–
pump having part number (P/N) 5916430 and paragraph (l)(2) of this AD. Information may 23, which applies to all Airbus SAS
a serial number identified in UTC Aerospace be emailed to: 9-ANM-116-AMOC-
Model A318, A319, A320, and A321
Systems Service Bulletin ERPS06M–29–22, REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate series airplanes. AD 2016–07–23
dated March 17, 2017, or Revision 1, dated requires, for certain airplanes, repetitive
June 27, 2017. principal inspector, or lacking a principal
(2) A serviceable part is a RAT hydraulic inspector, the manager of the local flight replacements of the fixed fairing upper
pump identified as acceptable in Airbus standards district office/certificate holding and lower attachment studs of both the
Service Bulletin A330–29–3130 or A340–29– district office. left-hand (LH) and right-hand (RH) main
4098, both dated May 3, 2017, as applicable. (2) Contacting the Manufacturer: For any landing gear (MLG); and repetitive
(3) Group 1 airplanes are airplanes on requirement in this AD to obtain corrective inspections for corrosion, wear, fatigue
which an affected part is installed. actions from a manufacturer, the action must cracking, and loose studs of each
(4) Group 2 airplanes are airplanes on be accomplished using a method approved
forward stud assembly of the fixed
which no affected part is installed. A Model by the Manager, International Section,
Transport Standards Branch, FAA; or The fairing door upper and lower forward
A330 airplane on which Airbus SAS
European Aviation Safety Agency (EASA); or attachments of both the LH and RH
Modification 206604 has been embodied in
production is a Group 2 airplane, provided Airbus SAS’s EASA DOA. If approved by the MLG; and replacement if necessary. AD
that the airplane remains in that DOA, the approval must include the DOA- 2016–07–23 also provides an optional
configuration. authorized signature. terminating modification for the
(l) Related Information repetitive replacements of the fixed
(h) Replacement and Re-identification for
fairing upper and lower attachment
Group 1 Airplanes (1) Refer to Mandatory Continuing
studs. Since we issued AD 2016–07–23,
(1) Within 18 months after the effective Airworthiness Information (MCAI) EASA AD
2018–0062, dated March 20, 2018, for related we have determined that for some
date of this AD; replace any affected RAT
information. This MCAI may be found in the airplane configurations, associated fixed
hydraulic pump with a serviceable part, in
accordance with the Accomplishment AD docket on the internet at http:// fairing assembly part numbers
Instructions of Airbus Service Bulletin A330– www.regulations.gov by searching for and susceptible to fatigue cracking were not
29–3130 or A340–29–4098, both dated May locating Docket No. FAA–2018–0764. listed in certain service information
3, 2017, as applicable. (2) For more information about this AD, required by AD 2016–07–23. In
(2) Concurrently with the replacement contact Vladimir Ulyanov, Aerospace addition, we have determined that
required by paragraph (h)(1) of this AD, re- Engineer, International Section, Transport additional work is necessary to re-
identify the part number of the serviceable Standards Branch, FAA, 2200 South 216th
identify the fixed fairing assembly part
RAT module, in accordance with the St., Des Moines, WA 98198; telephone and
fax: 206–231–3229. number on certain airplanes. This
Accomplishment Instructions of Airbus
(3) For service information identified in proposed AD would retain the
Service Bulletin A330–29–3130 or A340–29–
4098, both dated May 3, 2017, as applicable. this AD, contact Airbus SAS, Airworthiness requirements of AD 2016–07–23 and, for
Note 1 to paragraph (h)(2) of this AD: Office—EIAS, Rond-Point Emile Dewoitine certain airplanes, require re-
Airbus Service Bulletins A330–29–3130 and No: 2, 31700 Blagnac Cedex, France; identification of the LH and RH fixed
A340–29–4098, both dated May 3, 2017, telephone +33 5 61 93 36 96; fax +33 5 61 fairing assemblies’ part numbers. We are
provide guidance for re-identification of the 93 44 51; email account.airworth-eas@ proposing this AD to address the unsafe
part numbers of the RAT hydraulic pumps airbus.com; internet http://www.airbus.com. condition on these products.
that are not affected, and the part numbers You may view this service information at the
FAA, Transport Standards Branch, 2200 DATES: We must receive comments on
of the RAT modules that are not equipped
with an affected hydraulic pump. South 216th St., Des Moines, WA. For this proposed AD by October 15, 2018.
information on the availability of this ADDRESSES: You may send comments,
(i) Compliance With AD 2016–14–01 material at the FAA, call 206–231–3195. using the procedures found in 14 CFR
After re-identification of a RAT module on Issued in Des Moines, Washington, on 11.43 and 11.45, by any of the following
an airplane, as required by paragraph (h)(2) August 16, 2018. methods:
of this AD, the airplane remains compliant • Federal eRulemaking Portal: Go to
with the RAT module re-identification Michael Kaszycki,
Acting Director, System Oversight Division, http://www.regulations.gov. Follow the
requirements of AD 2016–14–01 for that
airplane. Aircraft Certification Service. instructions for submitting comments.
[FR Doc. 2018–18811 Filed 8–30–18; 8:45 am] • Fax: 202–493–2251.
(j) Parts Installation Prohibition
BILLING CODE 4910–13–P
• Mail: U.S. Department of
(1) For Group 1 airplanes: After Transportation, Docket Operations, M–
replacement of any affected RAT hydraulic 30, West Building Ground Floor, Room
pump as required by paragraph (h)(1) of this W12–140, 1200 New Jersey Avenue SE,
DEPARTMENT OF TRANSPORTATION
AD, do not install any affected RAT Washington, DC 20590.
hydraulic pump. • Hand Delivery: Deliver to Mail
Federal Aviation Administration
(2) For Group 2 airplanes: As of the
address above between 9 a.m. and 5
effective date of this AD, do not install any
affected RAT hydraulic pump. 14 CFR Part 39 p.m., Monday through Friday, except
Federal holidays.
(k) Other FAA AD Provisions [Docket No. FAA–2018–0762; Product
For service information identified in
Identifier 2018–NM–033–AD]
The following provisions also apply to this this NPRM, contact Airbus SAS,
AD: RIN 2120–AA64 Airworthiness Office—EIAS, Rond-
daltland on DSKBBV9HB2PROD with PROPOSALS
(1) Alternative Methods of Compliance Point Emile Dewoitine No: 2, 31700
(AMOCs): The Manager, International Airworthiness Directives; Airbus SAS Blagnac Cedex, France; telephone +33 5
Section, Transport Standards Branch, FAA, Airplanes 61 93 36 96; fax +33 5 61 93 44 51; email
has the authority to approve AMOCs for this
AD, if requested using the procedures found AGENCY: Federal Aviation account.airworth-eas@airbus.com;
in 14 CFR 39.19. In accordance with 14 CFR Administration (FAA), DOT. internet http://www.airbus.com. You
39.19, send your request to your principal may view this referenced service
ACTION: Notice of proposed rulemaking
inspector or local Flight Standards District information at the FAA, Transport
(NPRM).
Office, as appropriate. If sending information Standards Branch, 2200 South 216th St.,
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![Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Proposed Rules 44517
Des Moines, WA. For information on the the repetitive replacements of the fixed designed location stud, rod end and location
availability of this material at the FAA, fairing upper and lower attachment plate at the forward upper and lower leg
call 206–231–3195. studs. AD 2016–07–23 resulted from fixed-fairing positions. Subsequently, reports
were received of post-mod 27716/post-SB
reports of in-flight loss of fixed and
Examining the AD Docket A320–52–1100 MLG fixed fairing assemblies
hinged MLG fairings, and reports of with corrosion, which could also induce
You may examine the AD docket on post-modification MLG fixed fairing cracking.
the internet at http:// assemblies that have wear and This condition, if not detected and
www.regulations.gov by searching for corrosion. We issued AD 2016–07–23 to corrected, could lead to further cases of in-
and locating Docket No. FAA–2018– address in-flight detachment of an MLG flight detachment of a MLG fixed fairing,
0762; or in person at the Docket fixed fairing and consequent damage to possibly resulting in injury to persons on the
Management Facility between 9 a.m. the airplane. ground and/or damage to the aeroplane.
and 5 p.m., Monday through Friday, To address this potential unsafe condition,
except Federal holidays. The AD docket Actions Since AD 2016–07–23 Was EASA issued AD 2014–0096 to require
contains this NPRM, the regulatory Issued repetitive detailed inspections (DET) of the
MLG fixed fairings, and, depending on
evaluation, any comments received, and Since we issued AD 2016–07–23, we findings, accomplishment of applicable
other information. The street address for have determined that for some airplane corrective actions. That [EASA] AD also
the Docket Operations office (telephone configurations, associated fixed fairing prohibited installation of certain MLG fixed
800–647–5527) is in the ADDRESSES assembly part numbers susceptible to fairing rod end assemblies and studs as
section. Comments will be available in fatigue cracking were not listed in replacement parts on aeroplanes
the AD docket shortly after receipt. certain service information required by incorporating Airbus mod 27716 in
FOR FURTHER INFORMATION CONTACT: AD 2016–07–23. In addition, we have production, or modified in accordance with
Sanjay Ralhan, Aerospace Engineer, Airbus SB A320–52–1100 (any revision) in
determined that additional work is
International Section, Transport service.
necessary to re-identify the fixed fairing Since EASA AD 2014–0096 was issued,
Standards Branch, FAA, 2200 South assembly part number after completion Airbus developed an alternative inspection
216th St., Des Moines, WA 98198; of the optional terminating programme to meet the [EASA] AD
telephone and fax 206–231–3223. modification. This proposed AD would requirements. In addition, a terminating
SUPPLEMENTARY INFORMATION: retain the requirements of AD 2016–07– action (mod 155648) was developed, which
23 and require re-identification of the was made available for in-service aeroplanes
Comments Invited through Airbus SB A320–52–1165.
part number of the LH and RH fixed
We invite you to send any written fairing assemblies after completion of Consequently, EASA issued AD 2015–0001
relevant data, views, or arguments about (later revised), retaining the requirements of
the optional terminating modification.
this proposal. Send your comments to EASA AD 2014–0096, which was
The European Aviation Safety Agency superseded, and adding an optional
an address listed under the ADDRESSES (EASA), which is the Technical Agent terminating action for the repetitive
section. Include ‘‘Docket No. FAA– for the Member States of the European inspections. For post-mod aeroplanes, i.e.
2018–0762; Product Identifier 2018– Union, has issued EASA AD 2018–0023, incorporating Airbus mod 155648 in
NM–033–AD’’ at the beginning of your dated January 26, 2018; corrected production, or modified by Airbus SB A320–
comments. We specifically invite February 5, 2018 (referred to after this 52–1165 in service, the only remaining
comments on the overall regulatory, as the Mandatory Continuing requirement was to ensure that pre-mod
economic, environmental, and energy Airworthiness Information, or ‘‘the components are no longer installed.
aspects of this proposed AD. We will MCAI’’), to correct an unsafe condition Since EASA AD 2015–0001R1 [which
consider all comments received by the corresponds to FAA AD 2016–07–23] was
for all Airbus SAS Model A318 and issued, Airbus revised SB A320–52–1165 to
closing date and may amend this A319 series airplanes; all Airbus SAS
proposed AD based on those comments. include additional work, to re-identify the
Model A320–211, A320–212, A320–214, fairing assembly part number (P/N). During
We will post all comments we
A320–216, A320–231, A320–232, and the preparation of this additional work, it
receive, without change, to http://
A320–233 airplanes; and all Airbus SAS was noted that several configurations and
www.regulations.gov, including any associated P/N were not listed in the original
Model A321–111, A321–112, A321–131,
personal information you provide. We SB, which may have an impact on aeroplanes
A321–211, A321–212, A321–213, A321–
will also post a report summarizing each on which SB A320–52–1165 original issue or
231 and A321–232 airplanes. The MCAI
substantive verbal contact we receive Revision (rev.) 01 was already accomplished.
states:
about this proposed AD. It has also been noticed that the instructions
Several occurrences were reported of in- for reidentification of two P/N were not
Discussion flight loss of main landing gear (MLG) fixed correct in revision 02 of this SB.
We issued AD 2016–07–23, and hinged fairings. The majority of reported For the reasons described above, this
Amendment 39–18468 (81 FR 26115, events occurred following scheduled [EASA] AD retains the requirement of EASA
May 2, 2016) (‘‘AD 2016–07–23’’), for all maintenance activities. One result of the AD 2015–0001R1, which is superseded, but
investigation was that a discrepancy between requires using the SB at rev. 03.
Airbus SAS Model A318, A319, A320, the drawing and the maintenance manuals This [EASA] AD also requires
and A321 series airplanes. AD 2016–07– was discovered. The maintenance documents accomplishment of additional work [re-
23 requires, for certain airplanes, were corrected to prevent mis-rigging of the identification of the part number for the LH
repetitive replacements of the fixed MLG fixed and hinged fairings, which could and RH fixed fairing assemblies] for those
fairing upper and lower attachment induce fatigue cracking. aeroplanes on which parts were replaced in
studs of both the LH and RH MLG; and Prompted by these findings, Airbus issued accordance with the instructions of Airbus
daltland on DSKBBV9HB2PROD with PROPOSALS
repetitive inspections for corrosion, Service Bulletin (SB) A320–52–1083, SB A320–52–1165 at original issue, rev. 01 or
wear, fatigue cracking, and loose studs providing instructions for a one-time rev. 02 and correct (re)identification as
of each forward stud assembly of the inspection of the MLG fixed fairing applicable.
composite insert and the surrounding area,
fixed fairing door upper and lower replacement of the adjustment studs at the You may examine the MCAI in the
forward attachment of both the LH and lower forward position and adjustment to the AD docket on the internet at http://
RH MLG; and replacement if necessary. new clearance tolerances. That SB was www.regulations.gov by searching for
AD 2016–07–23 also provides an replaced by Airbus SB A320–52–1100 and locating Docket No. FAA–2018–
optional terminating modification for (modification (mod) 27716) introducing a re- 0762.
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Regulatory Findings (2) Model A319–111, A319–112, A319– AD at the latest of the times specified in
113, A319–114, A319–115, A319–131, A319– paragraphs (h)(1) through (h)(4) of this AD.
We determined that this proposed AD 132, and A319–133 airplanes. (1) Before the accumulation of 6,500 total
would not have federalism implications (3) Model A320–211, A320–212, A320– flight cycles since the airplane’s first flight.
under Executive Order 13132. This 214, A320–216, A320–231, A320–232, and (2) Within 6,500 flight cycles since the last
proposed AD would not have a A320–233 airplanes. installation of a pre-Airbus Modification
substantial direct effect on the States, on (4) Model A321–111, A321–112, A321– 27716 stud on the airplane.
the relationship between the national 131, A321–211, A321–212, A321–213, A321– (3) Within 1,500 flight cycles after June 6,
231 and A321–232 airplanes. 2016 (the effective date of AD 2016–07–23).
Government and the States, or on the
distribution of power and (d) Subject (4) Within 8 months after June 6, 2016 (the
responsibilities among the various Air Transport Association (ATA) of effective date of AD 2016–07–23).
levels of government. America Code 52, Doors. (i) Retained Repetitive Inspections, With No
For the reasons discussed above, I (e) Reason Changes
certify this proposed regulation: This AD was prompted by reports of in- This paragraph restates the requirements of
1. Is not a ‘‘significant regulatory flight loss of fixed and hinged main landing paragraph (i) of AD 2016–07–23, with no
action’’ under Executive Order 12866, gear (MLG) fairings, and reports of post- changes. For airplanes in post-Airbus
2. Is not a ‘‘significant rule’’ under the modification MLG fixed fairing assemblies Modification 27716 or post-Airbus Service
DOT Regulatory Policies and Procedures that have wear and corrosion. This AD was Bulletin A320–52–1100 configuration, with
(44 FR 11034, February 26, 1979), also prompted by a determination that for any of the components installed that are
some airplane configurations, associated identified in paragraphs (i)(1), (i)(2), and
3. Will not affect intrastate aviation in fixed fairing assembly part numbers (i)(3) of this AD: At the applicable
Alaska, and susceptible to fatigue cracking were not listed compliance time specified in paragraph (j) of
4. Will not have a significant in certain service information required by AD this AD, do a detailed inspection of the LH
economic impact, positive or negative, 2016–07–23. In addition, we have and RH MLG forward stud assemblies of the
on a substantial number of small entities determined that additional work is necessary fixed fairing door upper and lower forward
under the criteria of the Regulatory to re-identify the fixed fairing assembly part
attachments of both LH and RH MLG for
number on certain airplanes. We are issuing
Flexibility Act. indications of corrosion, wear, fatigue
this AD to prevent in-flight detachment of an
MLG fixed fairing and consequent damage to cracking, and loose studs, in accordance with
List of Subjects in 14 CFR Part 39 the Accomplishment Instructions of Airbus
the airplane.
Air transportation, Aircraft, Aviation Service Bulletin A320–52–1163, Revision 01,
safety, Incorporation by reference, (f) Compliance including Appendix 01, dated June 22, 2015.
Safety. Comply with this AD within the Repeat the detailed inspection thereafter at
compliance times specified, unless already intervals not to exceed 12 months.
The Proposed Amendment done. Replacement of both LH and RH MLG
forward stud assemblies on an airplane, in
Accordingly, under the authority (g) Retained Repetitive Replacements, With
No Changes accordance with the Accomplishment
delegated to me by the Administrator, Instructions of Airbus Service Bulletin A320–
the FAA proposes to amend 14 CFR part This paragraph restates the requirements of 52–1163, Revision 01, including Appendix
39 as follows: paragraph (g) of AD 2016–07–23, with no 01, dated June 22, 2015, extends the interval
changes. For airplanes in pre-Airbus for the next detailed inspection to 72 months;
PART 39—AIRWORTHINESS Modification 27716 and pre-Airbus Service
and the inspection must be repeated
DIRECTIVES Bulletin A320–52–1100 configuration, with
any of the components installed that are thereafter at intervals not to exceed 12
identified in paragraphs (g)(1) through (g)(5) months.
■ 1. The authority citation for part 39 (1) Stud—adjustment having P/N
of this AD: At the applicable compliance
continues to read as follows: D5285600720000.
time specified in paragraph (h) of this AD,
Authority: 49 U.S.C. 106(g), 40113, 44701. replace fixed fairing upper and lower (2) Rod end assembly (lower) having P/N
attachment studs of both left-hand (LH) and D5285600400000.
§ 39.13 [Amended] right-hand (RH) MLG, in accordance with the (3) Rod end assembly (upper) having P/N
■ 2. The FAA amends § 39.13 by Accomplishment Instructions of Airbus D5285600500000.
removing Airworthiness Directive (AD) Service Bulletin A320–52–1163, Revision 01,
including Appendix 01, dated June 22, 2015. (j) Retained Compliance Times for the
2016–07–23, Amendment 39–18468 (81 Requirements of Paragraph (i) of This AD,
Repeat the replacements thereafter at
FR 26115, May 2, 2016), and adding the intervals not to exceed 6,500 flight cycles. With No Changes
following new AD: (1) Plate—support having part number (P/ This paragraph restates the requirements of
Airbus SAS: Docket No. FAA–2018–0762; N) D5284024820000. paragraph (j) of AD 2016–07–23, with no
Product Identifier 2018–NM–033–AD. (2) Plate—support having P/N changes. For airplanes identified in
D5284024820200. paragraph (i) of this AD, except as provided
(a) Comments Due Date (3) Stud—adjustment having P/N by paragraph (o) of this AD: Do the initial
We must receive comments by October 15, D5284024420000. inspection required by paragraph (i) of this
2018. (4) Rod end assembly (lower) having P/N AD at the latest of the times specified in
D5284000500000. paragraphs (j)(1) through (j)(4) of this AD.
(b) Affected ADs (5) Rod end assembly (upper) having P/N (1) Before the accumulation of 72 months
This AD replaces AD 2016–07–23, D5284000600000.
since the airplane’s first flight.
Amendment 39–18468 (81 FR 26115, May 2,
(h) Retained Compliance Times for the (2) Within 72 months since the last
daltland on DSKBBV9HB2PROD with PROPOSALS
2016) (‘‘AD 2016–07–23’’).
Requirements of Paragraph (g) of This AD, installation of a post-Airbus Modification
(c) Applicability With No Changes 27716 assembly or since accomplishment of
This AD applies to the Airbus SAS This paragraph restates the requirements of the actions specified in Airbus Service
airplanes identified in paragraphs (c)(1) paragraph (h) of AD 2016–07–23, with no Bulletin A320–52–1100.
through (c)(4) of this AD, certificated in any changes. For airplanes identified in (3) Within 1,500 flight cycles after June 6,
category, all manufacturer serial numbers. paragraph (g) of this AD, except as provided 2016 (the effective date of AD 2016–07–23).
(1) Model A318–111, A318–112, A318– by paragraph (o) of this AD: Do the initial (4) Within 8 months after June 6, 2016 (the
121, and A318–122 airplanes. replacement required by paragraph (g) of this effective date of AD 2016–07–23).
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Revision 03, excluding Appendix 01 and (v) Other FAA AD Provisions South 216th St., Des Moines, WA. For
including Appendix 02, dated November 9, (1) Alternative Methods of Compliance information on the availability of this
2017, as applicable to the airplane (AMOCs): The Manager, International material at the FAA, call 206–231–3195.
configuration. Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this Issued in Des Moines, Washington, on
(s) New Terminating Action August 17, 2018.
AD, if requested using the procedures found
Modification of an airplane in accordance in 14 CFR 39.19. In accordance with 14 CFR Michael Kaszycki,
with the Accomplishment Instructions of 39.19, send your request to your principal Acting Director, System Oversight Division,
Airbus Service Bulletin A320–52–1165, inspector or local Flight Standards District Aircraft Certification Service.
Revision 03, excluding Appendix 01 and Office, as appropriate. If sending information [FR Doc. 2018–18813 Filed 8–30–18; 8:45 am]
including Appendix 02, dated November 9, directly to the International Section, send it
BILLING CODE 4910–13–P
2017, or as specified in paragraph (r) of this to the attention of the person identified in
AD constitutes terminating action for the paragraph (w)(2) of this AD. Information may
requirements of paragraphs (g), (i), (k), (l), be emailed to: 9-ANM-116-AMOC-
and (m) of this AD for that airplane. REQUESTS@faa.gov. DEPARTMENT OF ENERGY
(i) Before using any approved AMOC,
(t) New Parts Installation Prohibition notify your appropriate principal inspector, Federal Energy Regulatory
(1) Do not install on any airplane a or lacking a principal inspector, the manager Commission
component specified in paragraphs (g)(1) of the local flight standards district office/
through (g)(5) of this AD, as required by certificate holding district office. 18 CFR Part 284
paragraph (t)(1)(i) or (t)(1)(ii) of this AD, as (ii) AMOCs approved previously for AD
applicable. 2016–07–23 are approved as AMOCs for the [Docket No. RM96–1–041]
(i) For airplanes in pre-Airbus Modification corresponding provisions of this AD.
27716 or pre-Airbus Service Bulletin A320– (2) Contacting the Manufacturer: As of the Standards for Business Practices of
52–1100 configuration: After completing the effective date of this AD, for any requirement Interstate Natural Gas Pipelines
in this AD to obtain corrective actions from
optional modification specified in paragraph
a manufacturer, the action must be AGENCY: Federal Energy Regulatory
(n)(2) of this AD.
accomplished using a method approved by Commission.
(ii) For airplanes in post-Airbus the Manager, International Section, Transport
Modification 27716 or post Airbus Service ACTION: Notice of proposed rulemaking.
Standards Branch, FAA; or the European
Bulletin A320–52–1100 configuration: As of Aviation Safety Agency (EASA); or Airbus
the effective date of this AD. SUMMARY: The Federal Energy
SAS’s EASA Design Organization Approval
(2) Do not install on any airplane a Regulatory Commission (Commission) is
(DOA). If approved by the DOA, the approval
component specified in paragraphs (g)(1) must include the DOA-authorized signature. proposing to amend its regulations to
through (g)(5) of this AD or paragraphs (i)(1) (3) Required for Compliance (RC): Except incorporate by reference, with certain
through (i)(3) of this AD, as required by as specified by paragraph (q) of this AD: If enumerated exceptions, the latest
paragraph (t)(2)(i) or (t)(2)(ii) of this AD, as any service information contains procedures version (Version 3.1) of business
applicable. or tests that are identified as RC, those practice standards adopted by the
(i) For airplanes in pre-Airbus Modification procedures and tests must be done to comply Wholesale Gas Quadrant of the North
155648 or pre-Airbus Service Bulletin A320– with this AD; any procedures or tests that are American Energy Standards Board
52–1165, Revision 03, excluding Appendix not identified as RC are recommended. Those
(NAESB) applicable to natural gas
01 and including Appendix 02, dated procedures and tests that are not identified
as RC may be deviated from using accepted pipelines in place of the currently
November 9, 2017, configuration: After
methods in accordance with the operator’s incorporated version (Version 3.0) of
completion of the additional work required
by paragraph (r) of this AD. maintenance or inspection program without those business practice standards.
(ii) For airplanes in post-Airbus obtaining approval of an AMOC, provided DATES: Comments are due October 1,
Modification 155648 or post-Airbus Service the procedures and tests identified as RC can 2018.
Bulletin A320–52–1165, Revision 03, be done and the airplane can be put back in
an airworthy condition. Any substitutions or ADDRESSES: Comments, identified by the
excluding Appendix 01 and including
changes to procedures or tests identified as docket number of this proceeding, may
Appendix 02, dated November 9, 2017,
configuration: As of the effective date of this
RC require approval of an AMOC. be filed electronically at http://
AD. (w) Related Information www.ferc.gov in acceptable native
applications and print-to-PDF, but not
(u) Credit for Previous Actions (1) Refer to Mandatory Continuing
in scanned or picture format. For those
Airworthiness Information (MCAI) EASA AD
(1) This paragraph provides credit for 2018–0023, dated January 26, 2018; corrected unable to file electronically, comments
optional actions provided by paragraph (n)(2) February 5, 2018; for related information. may be filed by mail or hand-delivery
of this AD, if those actions were performed This MCAI may be found in the AD docket to: Federal Energy Regulatory
before the effective date of this AD using on the internet at http://www.regulations.gov Commission, Secretary of the
Airbus Service Bulletin A320–52–1100, by searching for and locating Docket No. Commission, 888 First Street NE,
dated December 7, 1998. FAA–2018–0762. Washington, DC 20426. The Comment
(2) This paragraph provides credit for the (2) For more information about this AD, Procedures Section of this document
actions required by paragraphs (g), (i), (k), (l), contact Sanjay Ralhan, Aerospace Engineer,
and (m) of this AD, if those actions were contains more detailed filing
International Section, Transport Standards
performed before the effective date of this AD procedures.
Branch, FAA, 2200 South 216th St., Des
using Airbus Service Bulletin A320–52–1163, Moines, WA 98198; telephone and fax 206– FOR FURTHER INFORMATION CONTACT:
dated February 4, 2014. 231–3223. Stanley Wolf (technical issues), Office of
daltland on DSKBBV9HB2PROD with PROPOSALS
(3) This paragraph provides credit for the (3) For service information identified in Energy Policy and Innovation, Federal
actions required by paragraphs (k), (l)(1), (m), this AD, contact Airbus SAS, Airworthiness Energy Regulatory Commission, 888
and (n)(3) of this AD if those actions were Office—EIAS, Rond-Point Emile Dewoitine
performed before the effective date of this AD
First Street NE, Washington, DC
No: 2, 31700 Blagnac Cedex, France;
using Airbus Service Bulletin A320–52–1165, telephone +33 5 61 93 36 96; fax +33 5 61
20426, Telephone: (202) 502–6841, E-
Revision 01, dated October 23, 2015, 93 44 51; email account.airworth-eas@ mail: stanley.wolf@ferc.gov.
excluding Appendix 01, dated November 3, airbus.com; internet http://www.airbus.com. Oscar F. Santillana (technical issues),
2014, and including Appendix 02, dated You may view this service information at the Office of Energy Market Regulation,
October 23, 2015. FAA, Transport Standards Branch, 2200 Federal Energy Regulatory
VerDate Sep<11>2014 16:46 Aug 30, 2018 Jkt 244001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\31AUP1.SGM 31AUP1](https://thefederalregister.org/doc/83_FR_44686/page/6.svg)
Document Created: 2018-08-31 00:53:01
Document Modified: 2018-08-31 00:53:01
| 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 October 15, 2018. | |
| 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. | |
| FR Citation | 83 FR 44516 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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