Airworthiness Directive · Amendment 39-14575 · Airbus Model A310-200 and -300 Series Airplanes
Airbus Model A310-200 and -300 Series Airplanes
Superseded. A later AD replaced this one: AD 2010-22-03. Comply with the one in force.
This AD applies to all Airbus Model A310-203, -204, -221, and -222 airplanes; and Model A310-304, -322, -324, and -325 airplanes; certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310-200 and -300 series airplanes. This AD requires doing repetitive rotating probe inspections for any crack of the rear spar internal angle and the left and right sides of the tee fitting, and doing related investigative/corrective actions if necessary. This AD also requires modifying the holes in the internal angle and tee fitting by cold expansion. This AD results from full-scale fatigue tests, which revealed cracks in the lower rear spar internal angle, and tee fitting. We are issuing this AD to detect and correct fatigue cracks of the rear spar internal angle and tee fitting, which could lead to the rupture of the internal angle, tee fitting, and rear spar, and consequent 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.
At the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, do a rotating probe inspection for any crack of the rear spar internal angle located in the center wing box and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, Revision 06, dated July 13, 2004, except as required by paragraphs (k), (l), and (m) of this AD. Do all applicable related investigative and corrective actions before further flight.
(1) Within 1,000 flight cycles or 1,600 flight hours after the effective date of this AD, whichever is first.
(2) At the applicable time specified in Table 1 of this AD.
| Airplane model and configuration | Threshold |
|---|---|
| Model A310-203, -204, -221, and -222 airplanes that are not modified by Airbus Modifications 06672S6812 and 07387S7974 | Before the accumulation of 10,300 total flight cycles or 16,600 total flight hours, whichever is first. |
| Model A310-203, -204, -221, and -222 airplanes that are modified by Airbus Modifications 06672S6812 and 07387S7974 (modified either in production or in accordance with Airbus Service Bulletin A310-57-2035) | Before the accumulation of 23,400 total flight cycles or 37,700 total flight hours, whichever is first. |
| Model A310-304, -322, -324, and -325 airplanes that are not modified by Airbus Modifications 06672S6812 and 07387S7974 | Before the accumulation of 9,500 total flight cycles or 15,000 total flight hours, whichever is first. |
| Model A310-304, -322, -324, and -325 airplanes that are modified by Airbus Modifications 06672S6812 and 07387S7974 (modified either in production or according to Airbus Service Bulletin A310-57-2035) | Before the accumulation of 21,500 total flight cycles or 34,000 total flight hours, whichever is first. |
(g) Repeat the inspection specified in paragraph (f) of this AD thereafter at the applicable time specified in paragraph (g)(1) or (g)(2) of this AD.
(1) For Model A310-203, -204, -221, and -222 airplanes: Repeat thereafter at intervals not to exceed 9,100 flight cycles or 14,650 flight hours, whichever is first.
(2) For Model A310-304, -322, -324, and -325 airplanes: Repeat thereafter at intervals not to exceed 9,500 flight cycles or 15,000 flight hours, whichever is first.
(h) At the applicable time specified in Table 2 of this AD or within 6 months after the effective date of this AD, whichever occurs later: Do a rotating probe inspection for any crack of the left and right sides of the tee fitting, and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, Revision 06, dated July 13, 2004, except as required by paragraphs (k), (l), and (m) of this AD. Do all applicable related investigative and corrective actions before further flight.
| Airplane model and configuration | Threshold |
|---|---|
| Model A310-203, -204, -221, and -222 airplanes that are not modified by Airbus Modification 06673S6813 | Before the accumulation of 21,600 total flight cycles or 34,800 total flight hours, whichever is first. |
| Model A310-203, -204, -221, and -222 airplanes that are modified by Airbus Modification 06673S6813 (modified either in production or in accordance with Airbus Service Bulletin A310-57-2035) | Before the accumulation of 41,300 total flight cycles or 66,500 total flight hours, whichever is first. |
| Model A310-304, -322, -324, and -325 airplanes that are not modified by Airbus Modification 06673S6813 | Before the accumulation of 17,100 total flight cycles or 27,000 total flight hours, whichever is first. |
| Model A310-304, -322, -324, and -325 airplanes that are modified by Airbus Modification 06673S6813 (modified either in production or in accordance with Airbus Service Bulletin A310-57-2035) | Before the accumulation of 32,300 total flight cycles or 51,000 total flight hours, whichever is first. |
(i) Repeat the inspection specified in paragraph (h) of this AD thereafter at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD.
(1) For Model A310-203, -204, -221, and -222 airplanes: Repeat thereafter at intervals not to exceed 10,800 flight cycles or 17,400 flight hours, whichever is first.
(2) For Model A310-304, -322, -324, and -325 airplanes: Repeat thereafter at intervals not to exceed 8,800 flight cycles or 13,900 flight hours, whichever is first.
For all airplanes except those that are modified by Airbus Modifications 06672S6812, 06673S6813, and 07387S7974 in production: Within 60 months after the effective date of this AD, modify the holes in the internal angle and tee fitting and do all applicable related investigative and corrective actions by accomplishing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A310-57-2035, Revision 08, dated September 19, 2005, except as required by paragraph (k) of this AD. Do all applicable related investigative and corrective actions before further flight.
Where Airbus Service Bulletin A310-57-2035, Revision 08, dated September 19, 2005; and Airbus Service Bulletin A310-57-2047, Revision 06, dated July 13, 2004; specify to contact the manufacturer if certain cracks are found, before further flight, repair those conditions according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).
All touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections.
Although Airbus Service Bulletin A310-57-2047, Revision 06, dated July 13, 2004, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2047, Revision 03, dated November 26, 1997; Revision 04, dated March 5, 1999; or Revision 05, dated August 3, 2000; are considered acceptable for compliance with the corresponding actions specified in paragraphs (f) through (i) of this AD.
(o) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2035, Revision 1, dated October 13, 1989; Revision 2, dated February 26, 1990; Revision 3, dated May 23, 1990; Revision 4, dated April 15, 1991; Revision 5, dated May 27, 1992; Revision 6, dated March 8, 1994; or Revision 7, dated April 17, 1996; are considered acceptable for compliance with the corresponding actions specified in paragraph (j) of this AD.
Accomplishing the initial inspections specified in paragraphs (f) and (g) of this AD terminates the requirements specified in paragraph (o) of AD 98-26-01.
