Airworthiness Directive · Amendment 39-15922 · Airbus Model A310 Series Airplanes
Airbus Model A310 Series Airplanes
This AD applies to Airbus Model A310 series airplanes, certificated in any category, on which Airbus Modifications 8888 and 8889 have not been accomplished.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A310 series airplanes. That AD currently requires repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; repetitive inspections for fatigue cracking of frame 39, stringer 35; and corrective actions if necessary. The existing AD also provides for an optional terminating action for certain repetitive inspections, except for certain areas where corrosion was detected and reworked. This new AD reduces the intervals for accomplishing repetitive inspections in a certain area. This AD results from mandatory continuing airworthiness information originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to detect and correct fatigue cracks and corrosion around and under the chafing plates of the wing root, which could result in reduced structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Except as provided by paragraphs (g), (k), and (l) of this AD: Within 4 years since date of manufacture, or within 12 months after June 3, 1998 (the effective date of AD 98-09-20, amendment 39-10501), whichever occurs later, perform an inspection to detect discrepancies around and under the chafing plates of the wing root, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; Revision 04, dated November 8, 2000; Revision 03, dated October 28, 1997; Revision 2, dated September 23, 1996; or Revision 1, dated September 19, 1995. If any discrepancy is found, prior to further flight, accomplish follow-on corrective actions (i.e., removal of corrosion, corrosion protection, high frequency eddy current inspection, x-ray inspection), as applicable, in accordance with the applicable service bulletin. Repeat the inspections thereafter at the intervals specified in the applicable service bulletin. After August 13, 2004 (the effective date of AD 2004-14-06), repeat the inspections thereafter at the intervals specified in Airbus Service Bulletin A310-53-2069, Revision 04, dated November 8, 2000; Airbus Service Bulletin A310-53-2069, Revision 05, dated November 12, 2002; or Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007.
(g) If any discrepancy is found during any inspection required by paragraph (f) of this AD, and Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; Revision 04, dated November 8, 2000; Revision 03, dated October 28, 1997; Revision 2, dated September 23, 1996; or Revision 1, dated September 19, 1995; as applicable; specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Where differences in the compliance times or corrective actions exist between the service bulletin and this AD, the AD prevails.
Except as provided by paragraph (i) of this AD: Accomplishment of the replacement of the stainless steel chafing plates with new chafing plates made of aluminum alloy, in accordance with Airbus Service Bulletin A310-53-2070, Revision 02, dated November 8, 2000; or the original issue, dated October 3, 1994; constitutes terminating action for the repetitive inspections required by paragraph (f) of this AD. Actions done in accordance with Airbus Service Bulletin A310-53-2070, Revision 1, dated September 23, 1996, are acceptable for compliance with actions required by this AD.
(i) Except as provided by paragraphs (k) and (l) of this AD: Within 30 days after August 13, 2004, do a review of the airplane maintenance records to determine if any corrosion was detected and reworked on the left and/or right side of frame 39, stringer 35, during the accomplishment of any corrective action or repair specified in paragraphs (f) or (g) of this AD. If any corrective action or repair has been accomplished in this area, perform an inspection for fatigue cracking of frame 39, stringer 35, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; or Revision 04, dated November 8, 2000. Do the initial inspection at the threshold specified in Figure 1 of the service bulletin, or within 30 days after August 13, 2004, whichever is later. Repeat the inspection thereafter at the intervals specified in Figure 1 of the service bulletin. If any discrepancy is found, prior to further flight, accomplish the applicable follow-on corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; or Revision 04, dated November 8, 2000.
Although the service bulletins specified in Table 1 of this AD specify to submit information to the manufacturer, this AD does not include such a requirement.
| Airbus Service Bulletin— | Revision— | Dated— |
|---|---|---|
| A310-53-2069 | 1 | September 19, 1995. |
| A310-53-2069 | 2 | September 23, 1996. |
| A310-53-2069 | 03 | October 28, 1997. |
| A310-53-2069 | 04 | November 8, 2000. |
| A310-53-2069 | 05 | November 12, 2002. |
| A310-53-2069 | 06 | May 22, 2007. |
| A310-53-2070 | Original | October 3, 1994. |
| A310-53-2070 | 1 | September 23, 1996. |
| A310-53-2070 | 02 | November 8, 2000. |
As of the effective date of this AD, use only the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007, to do the inspections and corrective actions required by paragraphs (f) and (i) of this AD.
As of the effective date of this AD, if any corrosion is found at frame 39, stringer 35, during any inspection required by this AD, do the repetitive inspections required by paragraphs (f) and (i) of this AD, as applicable, at the earlier of the times specified in paragraphs (l)(1) and (l)(2) of this AD. Repeat the inspections thereafter at intervals specified in Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007, except as provided by paragraph (m) of this AD.
(1) At the next specified repeat interval specified in paragraph (f) of this AD.
(2) At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD, except as provided by paragraph (m) of this AD.
(i) At the applicable threshold specified in Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007.
(ii) Within 900 flight cycles or 1,800 flight hours after the effective date of this AD, whichever occurs first.
(m) Where Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007, specifies to contact Airbus, do the inspections at threshold and repeat intervals approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
