2015-23-13: Auto Flight; Instruments

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 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): 2015-23-13 Airbus: Amendment 39-18330. Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-200-AD. (a) Effective Date This AD becomes effective December 29, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318-111, -112, -121, and -122 airplanes. (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. [[Page 73102]] (d) Subject Air Transport Association (ATA) of America Code 22, Auto Flight; 31, Instruments. (e) Reason This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. Exceeding allowable load could result in detachment of the vertical tail plane. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Pin Programming Modification Within 48 months after the effective date of this AD, modify the pin programming to activate the stop rudder input warning (SRIW) logic, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015. (h) Inspection To Determine Part Numbers (P/Ns), Flight Warning Computer (FWC) and Flight Augmentation Computer (FAC) Replacement Prior to or concurrently with the actions required by paragraph (g) of this AD: Inspect the part numbers of the FWC and the FAC installed on the airplane. If any FWC or FAC having a part number identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed on an airplane, prior to or concurrently with the actions required by paragraph (g) of this AD, replace all affected FWCs and FACs with a unit having a part number identified in paragraph (h)(3) of this AD, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraph (i) of this AD. (1) Paragraphs (h)(1)(i) through (h)(1)(xvii) of this AD identify FWCs having part numbers that are non-compatible with the SRIW activation required by paragraph (g) of this AD. (i) 350E017238484 (H1D1). (ii) 350E053020303 (H2E3). (iii) 350E016187171 (C5). (iv) 350E053020404 (H2E4). (v) 350E017248685 (H1D2). (vi) 350E053020606 (H2F2). (vii) 350E017251414 (H1E1). (viii) 350E053020707 (H2F3). (ix) 350E017271616 (H1E2). (x) 350E053021010 (H2F3P). (xi) 350E018291818 (H1E3CJ). (xii) 350E053020808 (H2F4). (xiii) 350E018301919 (H1E3P). (xiv) 350E053020909 (H2-F5). (xv) 350E018312020 (H1E3Q). (xvi) 350E053021111 (H2-F6). (xvii) 350E053020202 (H2E2). (2) Paragraphs (h)(2)(i) through (h)(2)(xxxiv) of this AD identify FACs having part numbers that are non-compatible with the SRIW activation required by paragraph (g) of this AD. (i) B397AAM0202. (ii) B397BAM0101. (iii) B397BAM0512. (iv) B397AAM0301. (v) B397BAM0202. (vi) B397BAM0513. (vii) B397AAM0302. (viii) B397BAM0203. (ix) B397BAM0514. (x) B397AAM0303. (xi) B397BAM0305. (xii) B397BAM0515. (xiii) B397AAM0404. (xiv) B397BAM0406. (xv) B397BAM0616. (xvi) B397AAM0405. (xvii) B397BAM0407. (xviii) B397BAM0617. (xix) B397AAM0506. (xx) B397BAM0507. (xxi) B397BAM0618. (xxii) B397AAM0507. (xxiii) B397BAM0508. (xxiv) B397BAM0619. (xxv) B397AAM0508. (xxvi) B397BAM0509. (xxvii) B397BAM0620. (xxviii) B397AAM0509. (xxix) B397BAM0510. (xxx) B397CAM0101. (xxxi) B397AAM0510. (xxxii) B397BAM0511. (xxxiii) B397CAM0102. (xxxiv) Soft P/N G2856AAA01 installed on hard P/N C13206AA00. (3) Paragraphs (h)(3)(i) through (h)(3)(v) of this AD identify the FWCs and FACs having the part numbers that are compatible with SRIW activation required by paragraph (g) of this AD. (i) For airplane configurations with no sharklet, an FAC having P/N B397BAM0621 (621 hard B). (ii) For airplanes configured with sharklet A320 and A319, an FAC having P/N B397BAM0622 (622 hard B). (iii) For airplanes configured with sharklet A321, an FAC having P/N B397BAM0623 (623 hardB). (iv) For all airplanes configured with an FAC standard CAA01, an FAC having soft P/N G2856AAA02 installed on hard P/N C13206AA00 (CAA02 hard C). (v) For all airplane configurations, an FWC having P/N 350E053021212 (H2-F7). (i) Service Information for Actions Required by Paragraph (h) of This AD Do the actions required by paragraph (h) of this AD in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (i)(1) through (i)(7) of this AD. (1) Airbus Service Bulletin A320-22-1375, dated January 15, 2014 (FAC 621 hard B). (2) Airbus Service Bulletin A320-22-1427, Revision 05, including Appendix 01, dated November 24, 2014 (FAC 622 hard B). (3) Airbus Service Bulletin A320-22-1447, Revision 03, dated April 21, 2015 (FAC CAA02 hard C). (4) Airbus Service Bulletin A320-22-1454, dated February 12, 2014 (FAC CAA02). (5) Airbus Service Bulletin A320-22-1461, Revision 07, including Appendix 01, datedMarch 23, 2015 (FAC 623 hard B). (6) Airbus Service Bulletin A320-22-1502, dated November 14, 2014 (FAC CAA02). (7) Airbus Service Bulletin A320-31-1414, Revision 03, dated September 15, 2014 (FWC H-F7). (j) Exclusion From Actions Required by Paragraphs (g) and (h) of This AD An airplane on which Airbus Modification 154473 has been embodied in production is excluded from the requirements of paragraphs (g) and (h) of this AD, provided that within 30 days after the effective date of this AD, an inspection of the part numbers of the FWC and the FAC installed on the airplane is done to determine that no FWC having a part number listed in paragraph (h)(1) of this AD, and no FAC having a part number listed in paragraph (h)(2) of this AD, has been installed on that airplane since date of manufacture. A review of airplane maintenance records is acceptable in lieu of this inspection if the part numbers of the FWC and FAC can be conclusively determined from that review. If any FWC or FAC having a part number identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed on a post-Airbus Modification 154473 airplane: Within 30 days after the effective date of this AD, do the replacement required by paragraph (h) of this AD. (k) Parts Installation Prohibitions After modification of an airplane as required by paragraphs (g), (h), and (j) of this AD: Do not install on that airplane any FWC having a part number listed in paragraph (h)(1) of this AD or any FAC having a part number listed in paragraph (h)(2) of this AD. (l) Later Approved Parts Installation of a version (part number) of the FWC or FAC approved after the effective date of this AD is an approved method of compliance with the requirements of paragraph (h) or (j) of this AD, provided the requirements specified in paragraphs (l)(1) and (l)(2) of this AD are met. (1) The version (part number) must be 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). (2) The installation must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (m) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-22- 1480, dated July 9, 2014; or Airbus Service Bulletin A320-22-1480, Revision 01, dated February 6, 2015. This service information is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the applicable Airbus service information identified in paragraphs (m)(2)(i) through (m)(2)(xviii) of [[Page73103]] this AD. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A320-22-1427, dated January 25, 2013. (ii) Airbus Service Bulletin A320-22-1427, Revision 01, dated July 30, 2013. (iii) Airbus Service Bulletin A320-22-1427, Revision 02, dated October 14, 2013. (iv) Airbus Service Bulletin A320-22-1427, Revision 03, dated November 8, 2013. (v) Airbus Service Bulletin A320-22-1427, Revision 04, dated February 11, 2014. (vi) Airbus Service Bulletin A320-22-1447, dated October 18, 2013. (vii) Airbus Service Bulletin A320-22-1447, Revision 01, dated September 18, 2014. (viii) Airbus Service Bulletin A320-22-1447, Revision 02, dated December 2, 2014. (ix) Airbus Service Bulletin A320-22-1461, dated October 31, 2013. (x) Airbus Service Bulletin A320-22-1461, Revision 01, dated February 25, 2014. (xi) Airbus Service Bulletin A320-22-1461, Revision 02, dated April 30, 2014. (xii) Airbus Service Bulletin A320-22-1461, Revision 03, dated July 17, 2014. (xiii) Airbus Service Bulletin A320-22-1461, Revision 04, dated September 15, 2014. (xiv) Airbus Service Bulletin A320-22-1461, Revision 05, dated November 13, 2014. (xv) Airbus Service Bulletin A320-22-1461, Revision 06, dated January 21, 2015. (xvi) Airbus Service Bulletin A320-31-1414, dated December 19, 2012. (xvii) Airbus Service Bulletin A320-31-1414, Revision 01, dated March 21, 2013. (xviii) Airbus Service Bulletin A320-31-1414, Revision 02, dated July 30, 2013. (n) Other FAA AD Provisions The following provisions also apply to this AD: (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: [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. The AMOC approval letter must specifically reference this AD. (2) 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. (3) 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0217R1, dated February 26, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0251-0003. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p(4) of this AD. (p) 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 Service Bulletin A320-22-1375, dated January 15, 2014. (ii) Airbus Service Bulletin A320-22-1427, Revision 05, including Appendix 01, dated November 24, 2014. (iii) Airbus Service Bulletin A320-22-1447, Revision 03, dated April 21, 2015. (iv) Airbus Service Bulletin A320-22-1454, dated February 12, 2014. (v) Airbus Service Bulletin A320-22-1461, Revision 07, including Appendix 01, dated March 23, 2015. (vi) Airbus Service Bulletin A320-22-1480, Revision 02,dated March 30, 2015. (vii) Airbus Service Bulletin A320-22-1502, dated November 14, 2014. (viii) Airbus Service Bulletin A320-31-1414, Revision 03, dated September 15, 2014. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. (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. (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.