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.
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Sec. 39.13 [Amended]
0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005), and adding the following new AD:
2014-20-18 Airbus: Amendment 39-17991. Docket No. FAA-2013-1064; Directorate Identifier 2012-NM-101-AD.
(a) Effective Date
This AD becomes effective December 11, 2014.
(b) Affected ADs
This AD replaces AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005).
(c) Applicability
This AD applies to Airbus Model B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4- 605R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; except airplanes on which Airbus Modification 12171 or 12249 has been embodied in production, or on which Airbus Service Bulletin A300-57-6069 has been embodied in service.
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Reason
This AD was prompted by reports of cracks found on the horizontal flange of the Frame 47 internal corner angle fitting while accomplishing the modification required by AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). We are issuing this AD to detect and correct fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.
(f) Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(g) Retained Inspections for Attachment Holes on the Internal Angles of the Wing Center Box, and Corrective Action
This paragraph restates the requirements of paragraphs (f), (g), and (h) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005), with revised service information. Perform a rotating probe inspection to detect cracking of the applicable attachment holes on the left and right internal angles of the wing center box in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004; or Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006. Do the inspection at the applicable time specified by paragraph 1.E.(2), Accomplishment Timescale, of Airbus Service Bulletin A300- 57-6049, Revision 06, dated July 15, 2004; except as required by paragraph (j) of this AD. Repeat the rotating probe inspection specified in this paragraph thereafter at intervals not to exceed the applicable interval specified in Airbus Service Bulletin A300- 57-6049, Revision 06, dated July 15, 2004, except that all touch- and-go landings must be counted in determining the total number of flight cycles between consecutive inspections. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.
(1) If no cracking is found during any inspection required by paragraph (g) of this AD: Prior to further flight, install new fasteners in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004; or Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.
(2) If any cracking is found during any inspection required by paragraph (g) of this AD: Prior to further flight,perform applicable corrective actions (including reaming, drilling, drill- stopping holes, chamfering, performing follow-on inspections, and installing new or oversize fasteners), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004; or Airbus Service Bulletin A300- 57-6049, Revision 07, dated December 22, 2006; except as required by paragraph (k) of this AD. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.
(h) Retained Inspections for Attachment Holes in the Horizontal Flange of the Internal Corner Angle Fitting of Fuselage Frame FR47, and Corrective Action
This paragraph restates the requirements of paragraphs (i), (j), and (k) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005), with revised service information. Perform a rotating probe inspection todetect cracking of the applicable attachment holes in the horizontal flange of the internal corner angle fitting of fuselage frame FR47, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002; or Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012. Do the inspection at the applicable time specified in paragraph 1.E., Compliance, of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002, except as provided by paragraph (j) of this AD; or within 1,500 flight cycles after July 8, 2002 (the effective date of AD 2002-11- 04, Amendment 39-12765 (67 FR 38193, June 3, 2002)); whichever occurs later. Repeat the rotating probe inspection specified in this paragraph thereafter at intervals not to exceed the applicable interval specified in Airbus Service Bulletin A300-57-6086, dated June 6, 2000, except that all touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.
(1) If no cracking is found during any inspection required by paragraph (h) of this AD: Prior to further flight, install new fasteners in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002; or Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.
(2) If any cracking is found during any inspection required by paragraph (h) of this AD: Prior to further flight, perform applicable corrective actions (including inspecting hole T if any cracking is found at hole G, reaming the holes, and installing oversize fasteners), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002; or Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012; except as required by paragraph (k) of this AD. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.
(i) Retained Modification of Angle Fittings of the Wing Center Box
This paragraph restates the requirements of paragraph (l) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). Modify the left and right internal angle fittings of the wing center box. The modification includes performing a rotating probe inspection to detect cracking, repairing cracks, cold expanding holes, and installing medium interference fitting bolts. Perform the modification in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001; and at the applicable time specified by paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001; except as required by paragraphs (j) and (k) of this AD.
(j) Retained Compliance Time Exception to Service Information Specified in Paragraphs (g), (h), and (i) of This AD
This paragraph restates the requirements of paragraph (m) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). Where the service information specified in paragraphs (g), (h), and (i) of this AD specify a grace period relative to receipt of the service bulletin, this AD requires compliance within the applicable grace period following December 19, 2005 (the effective date of AD 2005-23-08), if the threshold has been exceeded.
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(k) Retained Corrective Action Exception to Service Information Specified in Paragraphs (g), (h), and (i) of This ADThis paragraph restates the requirements of paragraph (n) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). If any crack is detected during any inspection required by paragraph (g), (h), or (i) of this AD, and the applicable service information specifies to contact the manufacturer for disposition of certain corrective actions: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent).
(l) Credit for Previous Actions
(1) This paragraph restates the credit provided by paragraph (o) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005): This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before December 19, 2005 (the effective date of AD 2005-23-08), using Airbus Service Bulletin A300-57-6086,dated June 6, 2000.
(2) This paragraph restates the credit provided by paragraph (p) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005): This paragraph provides credit for the modification required by paragraph (i) of this AD, if the modification was performed before December 19, 2005 (the effective date of AD 2005-23-08), using Airbus Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000.
(m) New Requirements of This AD: Repetitive Ultrasonic Inspections and Corrective Action
(1) For airplanes on which Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001, has not been done, or on which Airbus Modification 10155 has been done: Perform an ultrasonic inspection for cracking of the left- and right-hand aft bottom panel of the center wing box (CWB), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012. Do the inspection at the later of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD. If any cracking is found, 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). Repeat the inspection thereafter at intervals not to exceed the applicable interval specified in paragraph 1.E.(2), Accomplishment Timescale, of Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012.
(i) Within 13,400 flight cycles or 34,600 flight hours after the first flight of the airplane, whichever occurs first.
(ii) Within 650 flight cycles or 8 months after the effective date of this AD, whichever occurs first.
(2) For airplanes on which Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001, has been done: Perform an ultrasonic inspection for cracking of the left- and right-hand aft bottom panel of the center wing box (CWB), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012. Do the inspection at the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. If any cracking is found, 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). Repeat the inspection thereafter at intervals not to exceed the applicable interval specified in paragraph 1.E.(2), Accomplishment Timescale, of Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012.
(i) Within 13,400 flight cycles or 34,600 flight hours after accomplishing Airbus Service Bulletin A300-57-6050, whichever occurs first.
(ii) Within 650 flight cycles or 8 months after the effective date of this AD, whichever occurs first.
(n) New Reporting Requirement
Submit a report of the findings (both positive and negative) of the inspection required by paragraph (m) of this AD to the Design Approval Holder, at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of flight cycles and flight hours on the airplane. The inspection report form in Appendix 01 of Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, may be used.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
(o) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously in accordance with AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November14, 2005), are approved as AMOCs for the corresponding provision of 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 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 forthis 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.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) 2012-0092, dated May 25, 2012; Correction dated June 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-2013-10640002.
(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(5) and (q)(6) of this AD.
(q) 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 December 11, 2014.
(i) Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006.
(ii) Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012.
(4) The following service information was approved for IBR on December 19, 2005 (70 FR 69056, November 14, 2005).
(i) Airbus Service Bulletin A300-57-6049, excluding Appendix 01, Revision 06, dated July 15, 2004.
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(ii) Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001. This document contains the effective pages specified in paragraphs (q)(4)(ii)(A), (q)(4)(ii)(B),(q)(4)(ii)(C), and (q)(4)(ii)(D) of this AD.
(A) Pages 1, 4, 10A through 11, 75, and 76 are identified as Revision 03, dated May 31, 2001.
(B) Pages 2, 8, 9, 17 through 32, 41, 42, 57, 58, 61 through 63, and 77 are identified as Revision 02, dated February 10, 2000.
(C) Pages 3, 5 through 7, 10, 12, 33, 34, 37, 38, 47, 59, and 60 are identified as Revision 01, dated May 31, 1999.
(D) Pages 13 through 16, 35, 36, 39, 40, 43 through 46, 48 through 56, and 64 through 74 are identified as original, dated September 9, 1994.
(iii) Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002.
(5) The following service information was approved for IBR on July 8, 2002 (67 FR 38193, June 3, 2002).
(i) Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
(ii) Reserved.
(6) For service information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com.
(7) 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.
(8) 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.