Airworthiness Directive · Amendment 39-17528 · Wings
Airbus Airplanes
This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all serial numbers; except for airplanes identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Airplanes that have been modified in service according to Airbus Service Bulletin A310-57-2081 or during production by Airbus modification 12525.
(2) Airplanes that have been repaired according to Airbus Repair Inspection R573-49243 or R573-49237.
We are superseding airworthiness directive (AD) 2004-15-07, for certain Airbus Model A310 series airplanes. AD 2004-15-07 required repetitive inspections for fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors of the bottom skin panel of the wings, and related corrective action. AD 2004- 15-07 also provided for an optional terminating action to end the repetitive inspections. This new AD reduces the initial inspection compliance time and intervals, and provides additional terminating action options. This AD was prompted by a reassessment of a previous fatigue threshold and inspection interval, which resulted in a determination that reduced inspection thresholds and intervals for accomplishment of the tasks are necessary. We are issuing this AD to detect and correct fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reduced structural integrity of the wings.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
This paragraph restates the requirements of paragraph (a) of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). For airplanes on which Airbus Modification 5106 (Airbus Service Bulletin A310-57-2004, Revision 2, dated March 5, 1990, which is not incorporated by reference in this AD) has not been done as of August 31, 2004 (the effective date of AD 2004-15-07): Within 2,000 flight cycles after August 31, 2004 (the effective date of AD 2004-15-07), or within 3,000 flight cycles after the last inspection done per paragraph (k) of AD 98-26-01, Amendment 39-10942 (63 FR 69179, December 16, 1998), whichever is first; do a high frequency eddy current (HFEC) inspection for cracking of the area around the fasteners of the landing plate of the wing bottom skin panel No. 2 of the left and right wings. Do the inspection per the Accomplishment Instructions of Airbus Service Bulletin A310-57-2082, dated June 11, 2002. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 1,900 flight cycles, until accomplishment of the terminating action specified in paragraph (j) of this AD. Accomplishment of the inspection required by paragraph (k) of this AD terminates the requirements of paragraph (g) of this AD.
This paragraph restates the requirements of paragraph (b) of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). For airplanes on which Airbus Modification 5106 has been done as of August 31, 2004 (the effective date of AD 2004-15-07): Do the HFEC inspection required by paragraph (g) of this AD at the applicable time specified in paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 1,900 flight cycles, until accomplishment of the terminating action specified in paragraph (j) of this AD. Accomplishment of the inspection required by paragraph (k) of this AD terminates the requirements of paragraph (h) of this AD.
(1) For airplanes that have accumulated fewer than 17,000 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of August 31, 2004 (the effective date of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004)): Inspect prior to the accumulation of 18,000 total flight cycles.
(2) For airplanes that have accumulated 17,000 or more total flight cycles, but fewer than 19,001 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of August 31, 2004 (the effective date of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004)): Inspect within 2,000 flight cycles after August 31, 2004 (the effective date of AD 2004-15-07).
(3) For airplanes that have accumulated 19,001 or more total flight cycles, but fewer than 21,001 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of August 31, 2004 (the effective date of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004)): Inspect with 1,200 flight cycles after August 31, 2004 (the effective date of AD 2004-15-07).
(4) For airplanes that have accumulated 21,001 or more total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of August 31, 2004 (the effective date of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004)): Inspect within 500 flight cycles after August 31, 2004 (the effective date of AD 2004-15-07).
This paragraph restates the requirements of paragraph (c) of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, do the actions required by either paragraph (i)(1) or (i)(2) of this AD.
(1) Do a permanent repair of the area by doing the applicable corrective actions per the Accomplishment Instructions of Airbus Service Bulletin A310-57-2082, dated June 11, 2002. Accomplishment of the permanent repair terminates the repetitive inspections required by this AD for the repaired area only.
(2) Do the terminating action specified in paragraph (j) of this AD.
This paragraph restates the optional terminating action information specified in paragraph (d) of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004), with new service information and new options. Modification of the landing plate of the aileron access doors of the wing bottom skin panel No. 2 of the left and right wings by doing all the actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2081, dated June 11, 2002; or Airbus Service Bulletin A310-57-2081, Revision 03, dated October 13, 2010; or by doing the repair in accordance with Airbus Repair Instruction R573-49243, Revision C, dated July 16, 2003; or Airbus Repair Instruction R573-49237, Revision D, dated July 16, 2003; which terminates the requirements of this AD. Where Airbus Service Bulletin A310-57-2081, dated June 11, 2002; and Airbus Service Bulletin A310-57-2081, Revision 03, dated October 13, 2010; specify contacting the manufacturer for disposition of certain repair conditions that might be associated with the modification procedure, this AD requires that the repair be done in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegated agent).
Except as specified in paragraph (m)(1) of this AD, at the applicable time specified in Paragraph 1.E., “Compliance,” of Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010: Do an HFEC inspection to detect cracking of the area around the fasteners of the landing plate of the wing bottom skin panel No. 2 of the left and right wings; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, except as required by paragraph (m)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the area around the fasteners of the landing plate of the wing bottom skin panel number 2 of the left and right wings thereafter at the applicable intervals, including the compliance times for post temporary repair inspections, specified in Paragraph 1.E., “Compliance,” of Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, except as specified in paragraph (m)(3) of this AD. The temporary repair of cracks, as identified in Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, does not constitute terminating action for the repetitive inspections required by this AD. Accomplishment of the inspection required by this paragraph terminates the requirements of paragraphs (g) and (h) of this AD. Doing the modification specified in paragraph (j) of this AD terminates the repetitive inspections required by this paragraph.
For airplanes on which the temporary repair as specified in Airbus Mandatory Service Bulletin A310-57-2082 has been done: Within the applicable time specified in Paragraph 1.E., “Compliance,” of Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, do the permanent repair, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, except as provided by paragraph (m)(2) of this AD.
(1) Where Paragraph 1.E., “Compliance,” of Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, specifies a compliance time “from receipt of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) Where Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, specifies to contact Airbus for repair: Before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM-116; or EASA (or its delegated agent).
(3) Where Paragraph 1.E., “Compliance,” of Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, specifies to contact Airbus for inspection intervals, this AD requires using an inspection interval approved by either the Manager, International Branch, ANM-116; or EASA (or its delegated agent).
