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) 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), and adding the following new AD:
2016-07-17 Airbus: Amendment 39-18462. Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-AD.
(a) Effective Date
This AD becomes effective May 16, 2016.
(b) Affected ADs
This AD replaces AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997) (``AD 97-20-07'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers except those on which Airbus Modification 10160 has been done in production.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar. We are issuing this AD to detect and correct this fatigue cracking, which could reduce the residual strength of the top skin of the wings, and consequently affect the structural integrity of the airframe.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Retained Repetitive Inspections and Corrective Actions, With Revised Service Information
This paragraph restates the requirements of paragraph (a) of AD 97-20-07, with revised service information. For airplanes on which Airbus Modification 10089 has not been installed: Prior to the accumulation of 18,000 total landings, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct either a detailed visual inspection or a high frequency eddy current (HFEC) inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of thisAD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by paragraph (i) of this AD terminates the inspection requirements of this paragraph.
(1) If no cracking is detected, conduct repetitive inspections thereafter at the following intervals:
(i) If the immediately preceding inspection was conducted using detailed visual inspection techniques, conduct the next inspection within 5,000 landings.
(ii) If the immediately preceding inspection was conducted using HFEC techniques, conduct the next inspection within 9,500 landings.
(2) If any cracking is detected or suspected during any detailed visual inspection required by the introductory text of paragraph (g), paragraph (g)(1), or paragraph (g)(3)(i) of this AD, prior to further flight, confirm this finding and the length of this cracking by conducting an HFEC inspection, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. If no cracking is confirmed during the HFEC inspection, accomplish the repetitive inspection required by paragraph (g)(1)(ii) of this AD at the time specified in that paragraph.
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(3) If any cracking is detected or confirmed during any HFEC inspection required by the introductory text of paragraph (g), paragraph (g)(1), or paragraph (g)(2) of this AD:
(i) If the cracking is 75 millimeters (mm) or less per rib bay, prior to further flight, repair in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Thereafter, conduct repetitive detailed visual inspections of the repaired area at intervals not to exceed 50 landings, in accordance with Airbus Service Bulletin A300- 57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011.
(ii) If the cracking exceeds 75 mm per rib bay, prior to further flight, install Airbus Modification 10089, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Thereafter, conduct a low frequency eddy current (LFEC) inspection in accordance with the requirements of paragraph (h) of this AD.
Note 1 to paragraph (g) of this AD: Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994, references Airbus Service Bulletin A300-57-6041, Revision 4, dated November 16, 1995, as an additional source of guidance for installing Airbus Modification 10089.
(h) Retained Repetitive Inspections and Corrective Actions for Certain Airplanes, With Revised Service Information and Repair Instructions
This paragraph restates the requirements of paragraph (b) of AD 97-20-07, with revised service information and repair instructions. For airplanes on which Airbus Modification 10089 has been installed: Prior to the accumulation of 22,000 total landings after this modification has been installed, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct a LFEC inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Asof the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by paragraph (k) of this AD terminates the inspection requirements of this paragraph.
(1) If no cracking is detected, repeat this inspection thereafter at intervals not to exceed 11,000 landings.
(2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, Transport Airplane Directorate, FAA. As of the effective date of this AD, 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). Thereafter, repeat this inspection at intervals not to exceed 11,000 landings.
(i) New Requirement of This AD: Initial InspectionsFor airplanes on which Airbus Modification 10089 has not been installed: At the applicable time specified in paragraphs (i)(1) and (i)(2) of this AD, do either a detailed visual inspection or an HFEC inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (g) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before the accumulation of 14,000 total flight cycles or 30,300 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200 flighthours after the effective date of this AD, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Before the accumulation of 15,100 total flight cycles or 22,700 total flight hours, whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first.
(j) New Requirement of This AD: Repetitive Inspections
Repeat the inspections specified in paragraph (i) of this AD thereafter at the applicable interval specified in paragraphs (j)(1) and (j)(2) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the applicable interval specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD.
(i) For a detailed visual inspection, at intervals not to exceed 3,900 flight cycles or 8,400 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals not to exceed 7,400 flight cycles or 16,000 flight hours, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at the applicable interval specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) For a detailed visual inspection, at intervals not to exceed 4,200 flight cycles or 6,300 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals not to exceed 8,000 flight cycles or 11,900 flight hours, whichever occurs first.
(k) New Requirement of This AD: Initial Inspection for Certain Airplanes
For airplanes on which Airbus Modification 10089 has been installed: At the applicable time specified in paragraphs (k)(1) and (k)(2) of this AD, do an LFEC inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (h) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD.
(i) Before the accumulation of 17,000 total flight cycles or 37,100 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
(i) Before the accumulation of 18,500 total flight cycles or 27,800 total flight hours, whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first.
(l) New Requirement of This AD: Repetitive Inspections for Certain Airplanes
Repeat the inspection specified in paragraph (k) of this AD thereafter at the applicable interval specified in paragraphs (l)(1) and (l)(2) of this AD.
(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at intervals not to exceed 8,500 flight cycles or 18,500 flight hours, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5 hours, at intervals not to exceed 9,200 flight cycles or 13,700 flight hours, whichever occurs first.
(m) New Requirement of This AD: Corrective Actions
(1) If any cracking is detected or suspected during any detailed inspection required by paragraph (i) or (j) of this AD: Before further flight, confirm this finding and the length of
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this cracking by conducting an HFEC inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, except as specified in paragraph (o) of this AD. If no cracking is confirmed during the HFEC inspection, accomplish the applicable repetitive inspections required by paragraphs (j) and (l) of this AD at the applicable time specified in those paragraphs.
(2) If any cracking is found during any HFEC inspection required by paragraph (i), (j), or (m)(1) of this AD: Before further flight, do the applicable actions specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) If the cracking is 75 mm or less per each rib bay: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, except as specified in paragraph (o) of this AD. Do repetitive detailed inspections of the repaired area thereafter at intervals not to exceed 50 flight cycles or 110 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Within 250 flight cycles or 550 flight hours, whichever occurs first after doing the temporary repair, do a permanent repair of the repaired area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011.
(ii) If the cracking exceeds 75 mm per any rib bay: Before further flight, install Airbus Modification 10089, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Do an LFEC inspection thereafter at the intervals specified in paragraph (l) of this AD.
(3) If any cracking is found during any inspection required by this AD at fastener hole 1A, 1, or 2: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011.
(4) If any cracking is found during any LFEC inspection required by paragraph (k) or (l) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(n) Credit for Previous Actions
This paragraph provides credit for actions required by paragraphs (i) through (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-57-6044, Revision 03, dated April 7, 1999, including Appendix 01, Revision 03, dated April 7, 1999, which is not incorporated by reference in this AD.
(o) Exception to Service Information Specification
Although Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, specifies to submit information to Airbus, this AD does not require that submission.
(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: 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. 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.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0221, dated September 19, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searchingfor and locating Docket No. FAA-2015-1426.
(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(5) and (r)(6) 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.
(3) The following service information was approved for IBR on May 16, 2016
(i) Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on October 30, 1997 (62 FR 50251, September 25, 1997).
(i) Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994. Pages 1 through 8 of this document are identified as Revision 2, dated September 6, 1995; pages 9 and 10 are identified as original, dated March 1, 1993. Page 1 of Appendix 1 is identified as Revision 1, dated November 25, 1994; and pages 2 through 6 are identified as original, dated March 1, 1993.
(ii) Reserved.
(5) 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 account.airworth-eas@airbus.com; 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.