2018-23-02: Flight controls

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: [[Page 59283]] 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 adding the following new airworthiness directive (AD): 2018-23-02 Airbus SAS: Amendment 39-19488; Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD. (a) Effective Date This AD is effective December 28, 2018. (b) Affected ADs This AD affects AD 2007-06-02, Amendment 39-14983 (72 FR 12072, March 15, 2007) (``AD 2007-06-02''); and AD 2008-09-16, Amendment 39-15497 (73 FR 24160, May 2, 2008) (``AD 2008-09-16''). (c) Applicability This AD applies to Airbus SAS Model A318-111, A318-112, A318- 121, and A318-122 airplanes; Model A319-111, A319-112, A319-113,A319-114, A319-115, A319-131, A319-132, and A319-133 airplanes; Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes; certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Reason This AD was prompted by reports of missing assembly hardware on the trimmable horizontal stabilizer actuator (THSA). We are issuing this AD to address uncontrolled movement of the horizontal stabilizer as a result of the latent (undetected) failure of the THSA's primary load path and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Actions: Lower THSA Attachment Before exceeding 20 months since airplane first flight, or since airplane first flight following last THSA replacement, or within 20 months after the last inspection of the lower THSA attachment as specified in the instructions of Airbus Service Bulletin A320-27- 1164, Revision 02 up to Revision 09, whichever occurs latest, do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD concurrently, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018. Repeat the actions thereafter at intervals not to exceed 20 months. (1) Check the clearance between the secondary nut trunnions and the junction plates at the lower THSA attachment. (2) Do a general visual inspection of the lower THSA attachment for correct installation of attachment parts. (3) Do a general visual inspection of the THSA ball screw for dents. (h) Repetitive Inspections: Upper THSA Attachment Before exceeding 10 months since airplane first flight, or since airplane first flight following last THSA replacement, or within 10 months after the last inspection of the upper THSA attachment as specified in the instructions of Airbus Service Bulletin A320-27- 1164, Revision 02 up to Revision 09, whichever occurs latest, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD concurrently, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018. Repeat the inspections thereafter at intervals not to exceed 10 months. (1) Do a general visual inspection of the upper THSA attachment for correct installation, cracks, damage, and metallic particles. (2) Do a general visual inspection of the upper THSA attachment for correct installation of attachment parts. (i) Related Investigative and Corrective Actions If, during any action required by paragraph (g) or (h) of this AD, any discrepancy is detected (e.g., any installation deviation, cracking, damage, metallic particles, or dent is found), before further flight, accomplish all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018; except as required by paragraph (o)(1) of this AD. (j) Reporting Requirements for Actions Required by Paragraphs (g) and (h) of This AD In case of any findings during any action required by paragraph (g) or (h) of this AD, report the inspection results to Airbus SAS using the applicable ``Inspection Reporting Sheet'' of Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018, at the applicable time specified in paragraph (j)(1) or (j)(2) of this AD. If operators have reported findings as part of obtaining any corrective actions approved by the EASA Design Organization Approval (DOA), operators are not required to report those findings as specified in this paragraph. (1) If the inspection or check was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection or check was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (k) One-Time Inspection and Replacement For airplanes on which the THSA has been replaced or reinstalled since the date of issuance of the original certificate of airworthiness, or the date of issuance of the original export certificate of airworthiness: Within 6 months after the effective date of this AD, accomplish a detailed inspection of the THSA lower attachment gap clearances, in accordance with paragraphs 4.2.2 and 4.2.3 of Airbus Alert Operators Transmission (AOT) A27N010-17, Revision 01, dated October 17, 2017, including AOT Appendix_A27N010- 17. If the measured gap is less than 0.5 mm, before further flight, replace the THSA, including doing an inspection of the THSA parts to confirm the bushing is missing and applicable corrective actions, inaccordance with the instructions of Airbus AOT A27N010-17, Revision 01, dated October 17, 2017, including AOT Appendix_A27N010-17; and United Technologies Corporation (UTC) Aerospace Systems Repair Instructions RF-DSC-1361-17, Version 00, including Appendix A, dated May 24, 2017, as applicable, except as required by paragraph (o)(2) of this AD. (l) Definition of Groups For the purpose of this AD: Group 1 airplanes are those that, on the effective date of this AD, do not have the electrical load sensing device (ELSD) activated. Group 2 airplanes are those that, on the effective date of this AD, have the ELSD activated. (m) Activation and Concurrent Modification For Group 1 airplanes (see paragraph (l) of this AD): Do the actions specified in paragraphs (m)(1) and (m)(2) of this AD. (1) Within 4 years after the effective date of this AD, activate the ELSD of the THSA on the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1248, Revision 01, dated April 16, 2018. (2) Concurrently with or before the activation of the ELSD required by paragraph (m)(1) of this AD, modify the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1245, Revision 00, dated March 6, 2017; or Airbus Service Bulletin A320-27-1246, Revision 01, dated November 4, 2016; as applicable. (n) Concurrent Requirement for Airplanes Equipped With THSAs That do Not Have ELSDs For an airplane equipped with a THSA having a part number listed in figure 1 to paragraphs (n), (p), and (q) of this AD: Concurrently with or before the activation required by paragraph (m)(1) of this AD, modify the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1247, Revision 00, dated March 6, 2017. [[Page 59284]] [GRAPHIC] [TIFF OMITTED] TR23NO18.289 (o) Exceptions to Service Information (1) Where Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018, specifies to contact Airbus SAS for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (v)(2) of this AD. (2) Where Airbus AOT A27N010-17, Revision 01, dated October 17, 2017, specifies to contact Airbus SAS for appropriate action: Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (v)(2) of this AD. (p) Parts Installation Do not install on any airplane a THSA with a part number listed in figure 1 to paragraphs (n), (p), and (q) of this AD and do not deactivate the ELSD at the times specified in paragraph (p)(1) or (p)(2) of this AD, as applicable. (1) Group 1 airplanes (see paragraph (l) of this AD): After modification of the airplane as required by paragraph (m)(1) of this AD. (2) Group 2 airplanes (see paragraph (l) of this AD): Fromthe effective date of this AD. (q) Method of Compliance An airplane on which Airbus SAS Modification 155955 has been embodied in production is considered compliant with paragraphs (m)(1), (m)(2), and (n) of this AD, provided that it is determined that no THSA with a part number listed in figure 1 to paragraphs (n), (p), and (q) of this AD is installed on that airplane, and that the ELSD remains activated. A review of airplane maintenance records is acceptable to make this determination, provided those records can be relied upon for that purpose. (r) Airplanes Not Affected by the Requirements of Paragraph (k) of This AD The inspection required by paragraph (k) of this AD is not required for airplanes on which the THSA has been installed, as specified in the instructions of Airbus A320 Airplane Maintenance Manual (AMM) 27-44-51-400-001, dated May 2017, or subsequent. (s) Credit for Previous Actions (1) This paragraph provides credit for the initial actions required by paragraphs (g), (h), (i), and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-27-1164, Revision 10, dated March 27, 2014; Revision 11, dated December 15, 2014; Revision 12, dated March 23, 2016; or Revision 13, dated August 8, 2016. (2) This paragraph provides credit for actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A27N010-17, dated March 27, 2017. (3) This paragraph provides credit for actions required by paragraph (m)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-27- 1248, Revision 00, dated March 6, 2017. (4) This paragraph provides credit for actions required by paragraph (m)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-27- 1246, dated March 20, 2015. [[Page 59285]] (t) No Terminating Action for Repetitive Inspections in This AD Accomplishment on an airplane of the one-time inspection and replacement, as applicable, specified in paragraph (k) of this AD and the modifications specified in paragraphs (m)(1), (m)(2), and (n) of this AD, as applicable, do not constitute terminating action for the repetitive inspections required by paragraphs (g) and (h) of this AD for that airplane. (u) Terminating Action for Other FAA ADs Accomplishing the initial actions required by paragraphs (g) and (h) of this AD, and accomplishing the applicable actions required by paragraphs (i) and (j) of this AD, terminate all requirements of AD 2007-06-02 and AD 2008-09-16. (v) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (x)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Paperwork Reduction Act Burden Statement: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (4) Required for Compliance (RC): Except as specified in paragraph in (o)(1) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (w) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (x) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017-0237, dated December 4, 2017, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0298. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone and fax: 206-231-3223. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (y)(3) and (y)(5) of this AD. (y) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Alert Operators Transmission (AOT) A27N010-17, Revision 01, dated October 17, 2017, including AOT Appendix_A27N010- 17. (ii) Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018. (iii) Airbus Service Bulletin A320-27-1245, Revision 00, dated March 6, 2017. (iv) Airbus Service Bulletin A320-27-1246, Revision 01, dated November 4, 2016. (v) Airbus Service Bulletin A320-27-1247, Revision 00, dated March 6, 2017. (vi) Airbus Service Bulletin A320-27-1248, Revision 01, dated April 16, 2018. (vii) United Technologies Corporation Aerospace Systems (UTAS) United Technologies Corporation (UTC) Aerospace Systems Repair Instructions RF-DSC-1361-17, Version 00, including Appendix A, dated May 24, 2017. (3) For Airbus SAS 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. (4) For United Technologies Corporation Aerospace Systems service information identified in this AD, contact United Technologies Corporation Aerospace Systems: Goodrich Corporation, Actuation Systems, Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England; phone: +44 (0) 1902 624938; fax: +44 (0) 1902 788100; email: [email protected]; internet: http://www.goodrich.com/TechPubs. (5) 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. (6) 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.