2016-25-03: Doors

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): 2016-25-03 Airbus: Amendment 39-18729; Docket No. FAA-2016-6894; Directorate Identifier 2015-NM-120-AD. (a) Effective Date This AD is effective January 26, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 F4-605R and A300 F4-622R airplanes, certificated in any category, on which Airbus Modification 12046 has been embodied in production. Modification 12046 has been embodied in production on manufacturer serial numbers (MSNs) 0805 and above, except MSNs 0836, 0837, and 0838. (d) SubjectAir Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report of two adjacent frame forks that were found cracked on the aft lower deck cargo door (LDCD) of two Model A300-600F4 airplanes during scheduled maintenance. We are issuing this AD to detect and correct cracked or ruptured aft LDCD frames, which could allow loads to be transferred to the remaining structural elements. This condition could lead to the rupture of one or more vertical aft LDCD frames, which could result in reduced structural integrity of the aft LDCD. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Requirements At the applicable time specified in paragraph (h) of this AD, do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in accordance with Airbus Alert Operators Transmission (AOT) A52W011-15, Revision 00, dated July 23, 2015. (1) Do a one-time check of the aft LDCD clearances ``U'' and ``V'' between the latching hooks and the eccentric bush at FR60 through FR64A. If any value outside tolerance is found, adjust the latching hook before further flight. (2) Do a one-time detailed inspection to detect signs of wear of the hooks, eccentric bushes, and x-stops. If any wear is found, do all applicable corrective actions before further flight. (3) Do a high frequency eddy current (HFEC) inspection to detect cracking at all frame fork stations of the aft LDCD. If any crack is found, replace the cracked frame fork before further flight. Repeat the HFEC inspection thereafter at intervals not to exceed 600 flight cycles. (h) Compliance Times At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD, do the actions required by paragraph (g) of this AD. (1) Before the accumulation of 4,500 total flight cycles. (2) At the applicable time specified by paragraph (h)(2)(i) or (h)(2)(ii) of this AD. (i) For airplanes that have accumulated 8,000 or more total flight cycles as of the effective date this AD: Within 100 flight cycles after the effective date of this AD. (ii) For airplanes that have accumulated fewer than 8,000 total flight cycles as of the effective date of this AD: Within 400 flight cycles after the effective date of this AD. [[Page 93804]] (i) Reporting At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, report the findings (both positive and negative) of the clearance check and detailed inspection required by paragraphs (g)(1) and (g)(2) of this AD, and each HFEC inspection required by paragraph (g)(3) of this AD. Send the report to Airbus at Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or in accordance with paragraph 7 of Airbus AOT A52W011-15, Revision 00, dated July 23, 2015. The report must include the applicable information specified in Appendix 2 of Airbus AOT A52W011-15, Revision 00, dated July 23, 2015. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 60 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 60 days after the effective date of this AD. (j) Post-Repair Provisions (1) Accomplishment of corrective actions required by this AD does not terminate the repetitive HFEC inspections required by paragraph (g)(3) of this AD. (2) If all frame forks are replaced at the same time on the aft LDCD of an airplane, the next HFEC inspection required by paragraph (g)(3) of this AD can be deferred up to 4,500 flight cycles after the frame fork replacement. (k) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; 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. (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. (3) 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: 800Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (l) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) European Airworthiness Directive 2015-0152, dated July 24, 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-2016-6894. (m) 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 A52W011-15, Revision 00, dated July 23, 2015, including the following appendices: (A) Appendix 1--Flowchart, undated. (B) Appendix 2--Reporting Sheet, undated. (None of the pages of Appendix 2 are numbered.) (C) Appendix 3--titled ``Technical Disposition,'' Ref. TD/K12/ L3/02978/2015, Issue B, dated July 21, 2015. (Appendix 3 is identified with an appendix number only on page 1 of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015.) (D) Appendix 4--P/N identification for frame forks and bushings, undated. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 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.