2015-22-10: Stabilizers

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): 2015-22-10 Airbus: Amendment 39-18315. Docket No. FAA-2014-0574; Directorate Identifier 2013-NM-258-AD. (a) Effective Date This AD becomes effective December 15, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes specified 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. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Reason This AD was prompted by a report of skin disbonding on a composite side shell panel of a rudder. We are issuing this AD to detect and correct skin disbonding on the rudder, which could affect the structural integrity of the rudder, possibly resulting in reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine Repair Status Within 24 months after the effective date of this AD: Inspect the airplane maintenance records to determine if the rudder composite side shell panel has been repaired since first installation of the rudder on an airplane. (h) Inspection of Certain Repaired Rudders If the finding of the inspection required by paragraph (g) of this AD reveals that a rudder repair has been done as described in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014: Within 24 months after the effective date of this AD, do a pulse thermography inspection on the rudder, limited to the repaired area(s), to determine type, location, and size of the repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014. (i) Inspection of Rudders With No Records or Incomplete Records For each rudder for which maintenance records are not available or are incomplete: Do the actions required by paragraphs (i)(1) and (i)(2) of this AD. (1) Not later than 3 months before accomplishment of the pulse thermography inspection required by paragraph (i)(2) of this AD, send the serial number of each rudder to Airbus. (2) Within 24 months after the effective date of this AD, do a pulse thermography inspection on complete rudder side shells to identify and mark the repair location, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014. (j) Related Investigative Actions, Repetitive Inspections, and Corrective Actions After accomplishing the inspections required by paragraphs (h) and (i) of this AD, as applicable: Depending on findings, do the applicable actions specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, except as required by paragraph (l)(2) of this AD. Findings are specified in Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014. (1) Do all applicable related investigative actions and corrective actions at the applicable times specified in tables 3, 4A, 4B, 4C, 4D, and 5 in paragraph 1.E.(2), ``Accomplishment Timescale,'' of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, except as required by paragraph (l)(1) of this AD. (2) Do all applicable repetitive inspections of the restored and repaired areas at the applicable intervals specified in tables 3, 4A, 4B, 4C, 4D, and 5 in paragraph 1.E.(2), ``Accomplishment Timescale,'' of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014. (k) Airplanes Excluded From Certain Requirements Airplanes fitted with a rudder having a serial number which is not in the range TS-1001 to TS-1639 inclusive, or TS-2001 to TS-5890 inclusive; or is not TS-5927; are not affected by the requirements of paragraphs (h), (i), and (j) of this AD, provided it is determined that no repairs have been done as described in the structural repair manual (SRM) procedures identified in Figure A- GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, on the composite side shell panel of that rudder since first installation on an airplane. (l) Exceptions to Service Information (1) Where Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, specifies a compliance time ``after the original Service Bulletin issue date,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any damage or fluid ingress is found during any inspection required by this AD and Airbus Service Bulletin A320-55- 1041, Revision 01, dated February 24, 2014, specifies to contact Airbus: Before further flight, repair 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. (m) Parts Installation Limitation As of the effective date of this AD: Except for rudders that meet the requirements of paragraph (k) of this AD, do not install a rudder unless the rudder is inspected prior to installation as specified in paragraphs (h) and (i) of this AD, and all applicable corrective actions required by paragraph (j) of this AD are done. (n) Repair Prohibition As of the effective date of this AD, do not accomplish a composite side shell panel repair on any rudder using an SRM [[Page 69578]] procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014. (o) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (h), (i), and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-55-1041, dated November 26, 2012, which is not incorporated by reference in thisAD. (p) 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) 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. (3) ``RC'' Steps in Service Information: Except as required by paragraph (l)(2) 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. (4) Reporting Requirements: 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 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0302, dated December 19, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0574-0007. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD. (r) 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 A320-55-1041, Revision 01, dated February 24, 2014. (ii) Reserved. (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.