2015-02-14: Fuselage

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 removing Airworthiness Directive (AD) 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009), and adding the following new AD: 2015-02-14 Airbus: Amendment 39-18081. Docket No. FAA-2014-0139; Directorate Identifier 2012-NM-133-AD. (a) Effective Date This AD becomes effective April 6, 2015. (b) Affected ADs This AD replaces AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009). (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any category, all manufacturer serial numbers (MSNs). (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks on the main landing gear (MLG) door hinge fitting and actuator fitting on the keel beam. We are issuing this AD to detect and correct cracking on the MLG door hinge fitting and actuator fitting on the keel beam, which could lead to in-flight detachment of an MLG door, possibly resulting in injury to persons on the ground and/or damage to the airplane. [[Page 11100]] (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained One-Time Inspections and Corrective Action This paragraph restates the requirements of paragraphs (f)(1) and (f)(2) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009), with specific delegation approval language. For airplanes having serial numbers up to MSN 2850 inclusive, except MSNs 0115, 0184, 0782, 1151, 1190, 2650, 2675, 2706, 2801, and 2837: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD. (1) At the latest of the times specified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD: Perform detailed visual, high frequency eddy current (HFEC), and ultrasonic inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the left-hand (LH) and right-hand (RH) MLG door actuator fitting on the keel beam, and do all applicable corrective actions before further flight, except as provided by paragraph (h) of this AD. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, including Appendix 01, dated April 5, 2007; except where that service information specifies that the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. As of the effective date of this AD, where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (i) Within 6,000 flight cycles since first flight. (ii) Within 1,500 flight cycles after November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)). (iii) Within 6,000 flight cycles from the latest MLG door actuator fitting replacement. (2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: Perform detailed visual and HFEC inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door hinge fitting on the keel beam, and do all applicable corrective actions before further flight, except as provided by paragraph (h) of this AD. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1196, Revision 01, including Appendix 01, dated November 29, 2006; except where that service information specifies that the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. As of the effective date of this AD, where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, ANM- 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (i) Within 4,500 flight cycles since first flight. (ii) Within 1,500 flight cycles after November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)). (h) Retained Exception to Paragraph (g) of This AD This paragraph restates the exception specified in paragraph (f)(4) of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009). Where the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, including Appendix 01, dated April 5, 2007; or Airbus Mandatory Service Bulletin A320-53- 1196, Revision 01, including Appendix 01, dated November 29, 2006; as applicable; specify to submit a report where no damage or crack is found during the inspection required by paragraph (g)(1) or (g)(2) of this AD: Send the report to Airbus using the applicable reporting sheet in Appendix 01 of Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, dated April 5, 2007; or Airbus Mandatory Service Bulletin A320-53-1196, Revision 01, dated November 29, 2006. Send the report at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) If the inspection was done on or after November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)): Submit the report within 30 days after the inspection. (2) If the inspection was done before November 3, 2009 (the effective date of AD 2009-20-05, Amendment 39-16028 (74 FR 49795, September 29, 2009)): Submit the report within 30 days after November 3, 2009. (i) New Repetitive Inspections and Corrective Action (1) At the latest of the times specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD: Perform detailed, HFEC, and ultrasonic inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door actuator fitting on the keel beam, and do all applicable corrective actions before further flight. Do all actions requiredby this paragraph in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1195, Revision 05, dated November 22, 2013; except where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. Repeat the inspections thereafter at intervals not to exceed 2,250 flight cycles. (i) Before the accumulation of 3,000 flight cycles since first flight. (ii) Within 2,250 flight cycles after the most recent inspection done as described in Airbus Service Bulletin A320-53-1195, or Task 533154-02-1 of the Airbus A318/A319/A320/A321 Airworthiness Limitations Section Part 2--Damage Tolerant Airworthiness Limitations Items (DT ALI), as applicable. (iii) Within 1,500 flight cycles after the effective date of this AD. (2) At the latest of the times specified inparagraphs (i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of this AD: Perform detailed and HFEC inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door hinge fitting on the keel beam, and do all applicable corrective actions before further flight. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1196, Revision 04, dated November 22, 2013; except where that service information specifies that the applicable corrective action is contacting Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles. (i) Before the accumulation of 3,000 flight cycles since first flight. (ii) Within 3,000 flight cycles after the most recent inspection done as described in Airbus Service Bulletin A320-53-1196, or Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant Airworthiness Limitation Items (DT ALI), as applicable. (iii) Within 1,500 flight cycles after the effective date of this AD. (j) New Corrective Action Limitation The accomplishment of a corrective action on an airplane, as required by paragraph (i) of this AD, does not constitute terminating action for the repetitive inspection requirements of this AD for that airplane. (k) New Maintenance or Inspection Program Revision After the effective date of this AD and before further flight after doing the inspection required by paragraph (i) of this AD: Revise the maintenance or inspection program, as applicable, to remove Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision 01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated September 2010. The actions required by this AD take precedence over Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2-- Damage Tolerant Airworthiness Limitation Items (DT ALI), Revision 01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; and Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96 Issue 11, dated September 2010. [[Page 11101]] (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1195, Revision 03, dated November 8, 2011; or Airbus Service Bulletin A320-53-1195, Revision 04, dated August 22, 2012; which are not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (i)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1196, Revision 02, dated November 8, 2011; or Airbus Service Bulletin A320-53-1196, Revision 03, dated August 22, 2012; which are not incorporated by reference in this AD. (m) 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: 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required torespond 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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2012-0118, dated July 4, 2012, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0139-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD. (o) 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. (3) The following service information was approved for IBR on April 6, 2015. (i) Airbus Service Bulletin A320-53-1195, Revision 05, dated November 22, 2013. (ii) Airbus Service Bulletin A320-53-1196, Revision 04, dated November 22, 2013. (4) The following service information was approved for IBR on November 3, 2009 (74 FR 49795, September 29, 2009). (i) Airbus Mandatory Service Bulletin A320-53-1195, Revision 02, including Appendix 01, dated April 5, 2007. (ii) Airbus Mandatory Service Bulletin A320-53-1196, Revision 01, including Appendix 01, dated November 29, 2006. (5) 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. (6) 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. (7) 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.