AD 2017-05-12

We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.

Final rule.

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): \n\n2017-05-12 Airbus: Amendment 39-18823; Docket No. FAA-2016-6431; Directorate Identifier 2015-NM-182-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective April 17, 2017. \n\n(b) Affected ADs \n\n\n\tNone. \n\n(c) Applicability \n\n\n\tThis AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category; manufacturer serial numbers 4895, 4903, 4911, 4919, 4929, 4938, 4942, 4944, 4946, 4948, and 4951, 4956 through 5541 inclusive, 5544, 5547, 5550, 5551, 5553, 5556, 5559, 5561, 5562, 5563, 5565, 5566, 5570, 5572, 5576, and 5578. \n\t(1) Airbus Model A318-112 airplanes. \n\t(2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes. \n\t(3) Airbus Model A320-214, -232, and -233 airplanes. \n\t(4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 53, Fuselage. \n\n(e) Reason \n\n\n\tThis AD was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. We are issuing this AD to detect and replace structural parts made of aluminum alloy with inadequate heat treatment. This condition could result in reduced structural integrity of the airplane. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) One-time Measurement \n\n\n\tWithin 6 years since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness: Do a one-time eddy current conductivity measurement of the cabin, cargo compartment, and frame structural parts identified in the ''Affected P/N (part number)'' column of tables 1, 2, and 3 to paragraphs (g) and (i) of this AD to determine if aluminum alloy with inadequate heat treatment was used, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, except as required by paragraph (h) of this AD. \n\t(1) For cabin structural parts: Airbus Service Bulletin A320-53- 1292, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015. \n\t(2) For cargo compartment structural parts: Airbus Service Bulletin A320-53-1293, dated July 30, 2015; including Appendixes 01 and 02, dated July 30, 2015. \n\t(3) For frame structural parts: Airbus Service Bulletin A320-53- 1294, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015. \n\n\n\tTable 1 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/ \n\tInstalled \n\t(Airbus Service Bulletin A320-53-1292) ------------------------------------------------------------------------ \n\tAffected P/N Acceptable replacement P/N Area ------------------------------------------------------------------------ D2127245500000 D2127245500000 Cabin. D2127247600200 D2127247600200 Cabin. D2127247600300 D2127247600300 Cabin. D2127399900200 D2127399900200 Cabin. D2127399900300 D2127399900300 Cabin. D2127698900800 D2127698900800 Cabin. D2127698902400 D2127698902400 Cabin. D2527075131200 D2527075131251 Cabin. D2527075131300 D2527075131351 Cabin. D2527075138000 D2527075138000Cabin. D2527075138100 D2527075138100 Cabin. D2527075138200 D2527075138200 Cabin. D2527075138300 D2527075138300 Cabin. D2527075138600 D2527075138651 Cabin. D2527075138800 D2527075138851 Cabin. D2527240220600 D2527240220651 Cabin. D2527240220700 D2527240220751 Cabin. D2527240220800 D2527240220851 Cabin. D9249591201000 D9249591201000 Cabin. D9249591201800 D9249591201800 Cabin. D9249591227800 D9249591227851 Cabin. D9249591227900 D9249591227951 Cabin. D9249591228000 D9249591228051 Cabin. D9249591228100 D9249591228151 Cabin. ------------------------------------------------------------------------((Page 13385)) \n\n\n\n\n\tTable 2 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/ \n\tInstalled \n\t(Airbus Service Bulletin A320-53-1293) ------------------------------------------------------------------------ \n\tAffected P/N Acceptable replacement P/N Area ------------------------------------------------------------------------ D2707033520000 D2707033520000 Cargo. D2827027120000 D2827027120000 Cargo. D2827093500400 D2827093500400 Cargo. D2907013701200 D2907013701251 Cargo. D2907013800400 D2907013800451 Cargo. D3247012900000 D3247012900051 Cargo. D3817003820000 D3817003820000 Cargo. D3817012320200 D3817012320251 Cargo. D3837021201600 D3837021201600 Cargo. D3837033300400 D3837033300400Cargo. D4918518320200 D4918518320200 Cargo. D5347043420400 D5347043420451 Cargo. D9248511000000 D9248511000051 Cargo. D9249254100200 D9249254100251 Cargo. D9249282300000 D9249282300000 Cargo. ------------------------------------------------------------------------ \n\n\n\n\n\tTable 3 to Paragraphs (g) and (i) of This AD--Parts To Be Inspected/ \n\tInstalled \n\t(Airbus Service Bulletin A320-53-1294) ------------------------------------------------------------------------ \n\tAffected P/N Acceptable replacement P/N Area ------------------------------------------------------------------------ D2827098326800 D2827098326851 Frame. D5347051620600 D5347051620651 Frame. D5347051720600 D5347051720651 Frame. D5347057120000 D5347057120051Frame. D5347067520600 D5347067520651 Frame. D5347067521400 D5347067521451 Frame. D5347067520800 D5347067520851 Frame. D5347067521000 D5347067521051 Frame. D5347067521600 D5347067521651 Frame. D5347067620600 D5347067620600 Frame. D5347067720200 D5347067720251 Frame. D5347067720400 D5347067720451 Frame. D5347986520200 D5347986520251 Frame. ------------------------------------------------------------------------ \n\n(h) Exception to Paragraph (g) of This AD \n\n\n\tWhere Subtask 531293-832-207-001 of Airbus Service Bulletin A320-53-1293, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015, specifies inspecting Item 19 of Figure A-GVAAA for material heat treatment conformity, and that figure (incorrectly) identifies the inspection area for Item 19 as the four hinge brackets adjacent to the A-profile, this AD requires inspecting part number D491-85183-202-00, which is the A-profile, and not just the brackets. \n\n\n\tNote 1 to paragraph (h) of this AD: Airbus Technical Adaptation 80095365/011/2016, Issue 1, dated December 1, 2016 (''TA'') specifies that for Figure A-GVAAA, Sheet 01, of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, Item 19 should point to part number D491-85183-202-00 (and not just to the brackets). The TA also specifies that for Figure A-GRAAA, Sheet 01, of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, the correct Item 19 identification is part number D491-85183-202-00. \n\n(i) Replacement \n\n\n\tIf during the measurement required by paragraph (g) of this AD, any affected part number specified in table 1, 2, or 3 to paragraphs (g) and (i) of this AD is found to have a measured value greater than that specified in Figure A-GFAAA, Sheet 01, ''Inspection Flowchart,'' of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Before further flight, replace the affected part with the corresponding acceptable replacement part specified in table 1, 2, or 3 to paragraphs (g) and (i) of this AD, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. \n\n(j) No Reporting Requirement \n\n\n\tAlthough the service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. \n\n(k) Other FAA AD Provisions \n\n\n\tThe following provisions also apply to this AD: \n\t(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. \n\t(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. \n\t(3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. \n\n(l) Related Information \n\n\n\tRefer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0219, dated November 3, 2015, 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- 2016-6431. \n\n(m) Material Incorporated by Reference \n\n\n\t(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. \n\t(i) Airbus Service Bulletin A320-53-1292, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015. \n\t(ii) Airbus Service Bulletin A320-53-1293, dated July 30, 2015; including Appendixes 01 and 02, dated July 30, 2015. \n\t(iii) Airbus Service Bulletin A320-53-1294, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015. \n\t(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. \n\t(4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. \n\t(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Discussion \n\n\n\tWe issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318- 112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320- 214, -232, and -233 airplanes, and A321-211, -212, -213, -231, and -232 airplanes. The NPRM published in the Federal Register on May 11, 2016 (81 FR 29209). The NPRM was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. The NPRM proposed to require a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are issuing this AD to detect and replace structural parts made of aluminum alloy with inadequate heat treatment. This condition could result in reduced structural integrity of the airplane. \n\tThe European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0219, dated November 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ''the MCAI''), to correct an unsafe condition for certain Airbus Model A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, -213, -231, and -232 airplanes. The MCAI states: \n\n\n\tFollowing an Airbus quality control review on the final assembly line, it was discovered that aluminum alloy with inadequate heat treatment were delivered by a supplier for several structural parts. The results of the investigations highlighted that 1% of the stock could be impacted by this wrong material. \n\tStructural investigations demonstrated the capability to sustain the static limits loads, and sufficient fatigue life up to a certain inspection threshold. \n\tThis condition, if not detected and corrected, could reduce the aeroplane structural integrity following fatigue load. \n\tTo address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-53-1292, SB A320-53-1293, and SB A320-53- 1294 to provide inspection instructions. \n\tFor the reasons described above, this (EASA) AD requires a one- time Special Detailed Inspection (SDI) (i.e., eddy current conductivity measurement) of certain cabin, cargo compartment and frame parts (for material identification) and, depending on findings, replacement with serviceable parts. \n\n\n\tYou may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 6431. \n\nComments \n\n\n\tWe gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response. \n\nRequest To Include the Correctionin the Technical Adaptation to Certain Service Information \n\n\n\tVirgin America asked that we include the correction in Airbus Technical Adaptation (TA) 80095365/011/2016, Issue 1, dated December 1, 2016, to Figure A-GVAAA and Figure A-GRAAA of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, in this AD. Virgin America stated that the parts shown in Figure A-GVAAA and Figure A-GRAAA and highlighted for inspection are the four hinge brackets identified as having part number (P/N) ''D4918518320201, A-profile.'' However, the correct identification is P/N ''D4918518320200, A-profile.'' Virgin America noted that Airbus issued TA 80095365/011/2016, Issue 1, to update Figure A-GVAAA and Figure A-GRAAA of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, to identify the correct part number. Virgin America also stated that the TA specified that Airbus Service Bulletin A320-53-1293 is currently under revision and the correction will be included when the revision is issued.We agree with the commenter's request to include the specified correction. We have added a new paragraph (h) to this AD to provide an exception to Figure A-GVAAA of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, which is needed for compliance with paragraph (g) of this AD. However, Figure A-GRAAA, ''Reporting Sheet,'' of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, is not needed for compliance with this AD. We have added a note to paragraph (h) of this AD to provide the information in Airbus Technical Adaptation (TA) 80095365/011/2016, Issue 1, dated December 1, 2016, which specifies the corrected information for Figure A-GVAAA and Figure A-GRAAA of Airbus Service Bulletin A320-53-1293, dated July 30, 2015. We have also added paragraph (j) to clarify that reporting is not required by this AD; however, reporting is recommended for research and tracking. We have redesignated subsequent paragraphs accordingly. \n\nConclusion \n\n\n\tWe reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: \n\tAre consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and \n\tDo not add any additional burden upon the public than was already proposed in the NPRM. \n\tWe also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. \n\nRelated Service Information Under 1 CFR Part 51 \n\n\n\tWe reviewed the following service information: \n\tAirbus Service Bulletin A320-53-1292, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015. \n\tAirbus Service Bulletin A320-53-1293, dated July 30, 2015; including Appendixes 01 and 02, dated July 30, 2015. \n\tAirbus Service Bulletin A320-53-1294, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015. \n\tThe service information describes procedures for a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement of any affected part with a serviceable part. These documents are distinct since they \n\n((Page 13384)) \n\napply to different parts on the airplane. 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. \n\nCosts of Compliance \n\n\n\tWe estimate that this AD affects 46 airplanes of U.S. registry. \n\tWe also estimate that it takes about 6 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $23,460, or $510 per product. \n\tWe have received no definitive data that enables us to provide cost estimates for the on-condition actions specified in this AD. \n\tAccording to the manufacturer, some 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 available costs in our cost estimate. \n\nAuthority for This Rulemaking \n\n\n\tTitle 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. \n\tWe 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, andprocedures 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. \n\nRegulatory Findings \n\n\n\tWe determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. \n\tFor the reasons discussed above, I certify that this AD: \n\t1. Is not a ''significant regulatory action'' under Executive Order 12866; \n\t2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); \n\t3. Will not affect intrastate aviation in Alaska; and \n\t4. 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. \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.