Airworthiness Directive · Amendment 39-16482 · Wings
Airbus Model A310 Series Airplanes
This AD applies to all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For all airplanes except those that are modified by Airbus Modifications 06672S6812, 06673S6813, and 07387S7974 in production: Within 60 months after June 7, 2006 (the effective date of AD 2006-09-05), 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; or Airbus Mandatory Service Bulletin A310-57-2035, Revision 10, dated March 25, 2008; except as required by paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2035, Revision 10, dated March 25, 2008.
Where the service information specified in Table 1 of this AD specifies 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); or EASA (or its delegated agent).
| Document | Revision | Date |
|---|---|---|
| Airbus Mandatory Service Bulletin A310-57-2035 | 10 | March 25, 2008. |
| Airbus Service Bulletin A310-57-2035 | 08 | September 19, 2005. |
(i) Actions accomplished before June 7, 2006, in accordance with the service information specified in Table 2 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD.
| Document | Revision | Date |
|---|---|---|
| Airbus Service Bulletin A310-57-2035 | 1 | October 13, 1989. |
| Airbus Service Bulletin A310-57-2035 | 2 | February 26, 1990. |
| Airbus Service Bulletin A310-57-2035 | 3 | May 23, 1990. |
| Airbus Service Bulletin A310-57-2035 | 4 | April 15, 1992. |
| Airbus Service Bulletin A310-57-2035 | 5 | May 27, 1992. |
| Airbus Service Bulletin A310-57-2035 | 6 | March 8, 1994. |
| Airbus Service Bulletin A310-57-2035 | 7 | April 17, 1996. |
For airplanes on which an inspection of the rear spar internal angle has not been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the later of the times specified in paragraphs (j)(1) and (j)(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 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 4 of this AD. Certain compliance times are applicable to short range use, average flight time (AFT) equal to or less than 4 hours, or long range use, AFT exceeding 4 hours.
Note 1: To establish the AFT, divide the accumulated flight time (counted from the take-off up to the landing) by the number of accumulated flight cycles. This gives the average flight time per flight cycle.
(1) Within the applicable time specified in Table 3 of this AD.
(2) Within the applicable time specified in paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD:
(i) For A310-203, -204, -221, and -222 airplanes: Within 700 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first.
(ii) For A310-304, -322, -324, and -325 short range airplanes: Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first.
(iii) For A310-304, -322, -324, and -325 long range airplanes: Within 500 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first.
| Model and configuration | Compliance time (whichever occurs first) | |
| A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done | Before the accumulation of 9,200 total flight cycles | Before the accumulation of 18,500 total flight hours. |
| A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in production | Before the accumulation of 19,800 total flight cycles | Before the accumulation of 39,600 total flight hours. |
| A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 6,200 total flight cycles and 12,500 total flight hours | Within 19,800 flight cycles after the effective date of this AD | Within 39,600 flight hours after the effective date of this AD. |
| A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and are not done before the accumulation of 6,200 total flight cycles and 12,500 total flight hours | Within 8,200 flight cycles after the effective date of this AD | Within 16,400 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done | Before the accumulation of 7,500 total flight cycles | Before the accumulation of 21,100 total flight hours. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done | Before the accumulation of 5,300 total flight cycles | Before the accumulation of 26,900 total flight hours. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done | Before the accumulation of 15,900 total flight cycles | Before the accumulation of 44,700 total flight hours. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in production | Before the accumulation of 11,300 total flight cycles | Before the accumulation of 56,900 total flight hours. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 4,700 total flight cycles and 13,100 total flight hours | Within 15,900 flight cycles after the effective date of this AD | Within 44,700 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and not done before the accumulation of 4,700 total flight cycles and 13,100 total flight hours | Within 8,500 flight cycles after the effective date of this AD | Within 23,800 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 before the accumulation of 3,300 total flight cycles and 16,700 total flight hours | Within 11,300 flight cycles after the effective date of this AD | Within 56,900 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and not done before the accumulation of 3,300 total flight cycles and 16,700 total flight hours | Within 6,000 flight cycles after the effective date of this AD | Within 30,300 flight hours after the effective date of this AD. |
| Model and configuration | Interval (not to exceed) |
|---|---|
| A310-203, -204, -221, and -222 airplanes | Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first. |
| A310-304, -322, -324, and -325 short range airplanes | Within 6,800 flight cycles or 19,100 flight hours, whichever occurs first. |
| A310-304, -322, -324, and -325 long range airplanes | Within 4,800 flight cycles or 24,300 flight hours, whichever occurs first. |
(k) For airplanes on which an inspection of the rear spar internal angle has been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the applicable time specified in paragraphs (k)(1), (k)(2), and (k)(3) 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 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 4 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours.
(1) For A310-203, -204, -221, and -222 airplanes: At the earlier of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD.
(i) Within 7,940 flight cycles or 15,880 flight hours after the most recent inspection, whichever occurs first.
(ii) At the later of the times specified in paragraphs (k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD.
(A) Within the applicable interval specified in Table 4 of this AD.
(B) Within 740 flight cycles or 1,480 flight hours after the effective date of this AD, whichever occurs first.
(2) For A310-304, -322, -324, and -325 short range airplanes: At the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
(i) Within the applicable interval specified in Table 4 of this AD.
(ii) Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first.
(3) For A310-304, -322, -324, and -325 long range airplanes: At the later of the times specified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD.
(i) Within the applicable interval specified in Table 4 of this AD.
(ii) Within 500 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first.
For airplanes on which an inspection of the left and right sides of the tee fitting has not been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD, 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 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 6 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours.
(1) Within the applicable time specified in Table 5 of this AD.
(2) Within the applicable time in paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD.
(i) For A310-203, -204, -221, and -222 airplanes: Within 800 flight cycles or 1,600 flight hours, whichever occurs first.
(ii) For A310-304, -322, -324, and -325 short range airplanes: Within 800 flight cycles or 2,200 flight hours, whichever occurs first.
(iii) For A310-304, -322, -324, and -325 long range airplanes: Within 600 flight cycles or 3,100 flight hours, whichever occurs first.
| Model and configuration | Compliance time (whichever occurs first) | |
| A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is not done | Before the accumulation of 14,300 flight cycles | Within 28,700 flight hours after the effective date of this AD. |
| A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is done in production | Before the accumulation of 17,500 total flight cycles | Before the accumulation of 35,000 total flight hours. |
| A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 8,100 total flight cycles and 16,200 total flight hours | Within 17,500 flight cycles after the effective date of this AD | Within 35,000 flight hours after the effective date of this AD. |
| A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and not before the accumulation of 8,100 total flight cycles and 16,200 total flight hours | Within 9,600 flight cycles after the effective date of this AD | Within 19,200 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is not done | Within 10,800 flight cycles after the effective date of this AD | Within 30,400 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is not done | Before the accumulation of 8,500 total flight cycles | Before the accumulation of 42,800 total flight hours. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is done in production | Before the accumulation of 13,100 total flight cycles | Before the accumulation of 36,700 total flight hours. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is done in production | Before the accumulation of 10,300 total flight cycles | Before the accumulation of 51,600 total flight hours. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 5,800 total flight cycles and 16,400 total flight hours | Within 13,100 flight cycles after the effective date of this AD | Within 36,700 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and not before the accumulation of 5,800 total flight cycles and 16,400 total flight hours | Within 7,400 flight cycles after the effective date of this AD | Within 20,900 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 4,600 total flight cycles and 23,100 total flight hours | Within 10,300 flight cycles after the effective date of this AD | Within 51,600 flight hours after the effective date of this AD. |
| A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and not before the accumulation of 4,600 total flight cycles and 23,100 total flight hours | Within 6,000 flight cycles after the effective date of this AD | Within 30,300 flight hours after the effective date of this AD. |
| Model and configuration | Interval (not to exceed) |
|---|---|
| A310-203, -204, -221, and -222 airplanes | 9,100 flight cycles or 18,300 flight hours, whichever occurs first. |
| A310-304, -322, -324, and -325 short range airplanes | 7,300 flight cycles or 20,400 flight hours, whichever occurs first. |
| A310-304, -322, -324, and -325 long range airplanes | 5,900 flight cycles or 29,600 flight hours, whichever occurs first. |
(m) For airplanes on which an inspection of the rear left and right sides of the tee fitting has been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the applicable time specified in paragraphs (m)(1) or (m)(2) of this AD, 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 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 6 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours.
(1) For A310-203, -204, -221, and -222 airplanes: At the earlier of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD.
(i) Within 10,800 flight cycles or 17,400 flight hours after the most recent inspection, whichever occurs first.
(ii) At the later of the times specified in paragraphs (m)(1)(ii)(A) and (m)(1)(ii)(B) of this AD.
(A) Within the applicable interval specified in Table 6 of this AD.
(B) Within 700 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first.
(2) For A310-304, -322, -324, and - 325 airplanes: At the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) Within the applicable interval specified in Table 6 of this AD.
(ii) Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first.
Where Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009, specifies 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 EASA (or its delegated agent).
Although Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
(p) Actions accomplished before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A310-57-2035, Revision 09, dated September 27, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD.
(q) Actions accomplished before the effective date of this AD in accordance with the service information specified in Table 7 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraphs (j) through (m) of this AD.
| Document | Revision | Date |
|---|---|---|
| Airbus Service Bulletin A310-57-2047 | 03 | November 26, 1997. |
| Airbus Service Bulletin A310-57-2047 | 04 | March 5, 1999. |
| Airbus Service Bulletin A310-57-2047 | 05 | August 3, 2000. |
| Airbus Service Bulletin A310-57-2047 | 06 | July 13, 2004. |
| Airbus Service Bulletin A310-57-2047 | 07 | March 14, 2008. |
Accomplishing a rotating probe inspection of the rear spar internal angle and the tee fitting in accordance with Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009, or a service bulletin listed in Table 7 of this AD, terminates the requirements specified in paragraph (o) of AD 98-26-01.
Note 2: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information tells you to contact the manufacturer for repair information, paragraph (n) of this AD requires that you contact the FAA or EASA (or its delegated agent) instead. Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (o) of this AD specifies that such submittal is not required.
