Airworthiness Directive · Amendment 39-16688 · Wings
Airbus Model A310 Series Airplanes
This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all certified models, all serial numbers.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCA I) 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 Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification No. 05101 has been embodied in production, or on which Airbus Service Bulletin A310-57-2003 has been embodied in service before the accumulation of 9,400 total flight cycles and 18,800 total flight hours: At the times specified in paragraph (h) of this AD, perform a detailed visual inspection to detect cracks in the external surface of the wing lower skin around the landing access panel holes of the leading edge, in accordance with the Airbus Service Bulletin A310-57-2002, Revision 1, dated July 2, 1992; Airbus Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996; or Airbus Mandatory Service Bulletin A310-57-2002, Revision 03, dated November 28, 2006. If any discrepancy is found, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent) or EASA (or its delegated agent). Except as required by paragraph (n) of this AD, repeat the detailed inspection specified in this paragraph at the earlier of the times specified in paragraphs (g)(1) and (g)(2) of this AD; and thereafter at intervals not to exceed 2,300 flight cycles or 4,700 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2002, Revision 03, dated November 28, 2006. Accomplishment of Airbus Modification 05101 before the effective date of this AD terminates the repetitive inspection requirements of this paragraph; however, airplanes identified in paragraph (n) of this AD are applicable to the new inspections required by paragraph (n) of this AD. As of the effective date of this AD: Accomplishment of Airbus Modification 05101 before the accumulation of 9,400 total flight cycles and 18,800 total flight hours terminates the repetitive inspection requirements of this paragraph.
Note 1: Airbus Service Bulletin A310-57-2003, Revision 03, dated October 16, 2006, is an additional source of guidance for accomplishing Airbus Modification 05101.
Note 2: As of the effective date of this AD, if Airbus Service Bulletin A310-57-2003 is done on or after the accumulation of 9,400 total flight cycles or on or after the accumulation of 18,800 total flight hours, the actions specified in paragraph (g) of this AD are still required.
(1) Within 3,000 flight cycles after doing the detailed inspection specified in paragraph (g) of this AD.
(2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within 2,300 flight cycles or 4,700 flight hours, whichever occurs first, after doing the detailed inspection required by paragraph (g) of this AD.
(ii) Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD.
(h) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification No. 05101 has been embodied in production, or on which Airbus Service Bulletin A310-57-2003 has been embodied in service before the accumulation of 9,400 total flight cycles and 18,800 total flight hours: At the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, do the detailed inspection required by paragraph (g) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999 (the effective date of AD 98-26-01, amendment 39-10942), whichever occurs later.
(2) At the later of the times specified in paragraph (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Prior to the accumulation of 9,400 total flight cycles or 18,800 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD.
(i) For Model A310-203, A310-204, A310-222, A310-304, A310-322, A310-324, and A310-325 airplanes that are listed in Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996, and are identified as Configuration 1 in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007: Prior to the accumulation of 6,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later, perform an eddy current inspection to detect cracks in the holes around the overwing refueling aperture at ribs 13-14, in accordance with Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007. If any discrepancy is found, prior to further flight, perform follow-on corrective actions, as applicable, in accordance with Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007; except where the service bulletin specifies to contact Airbus for repair, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the DGAC (or its delegated agent) or EASA (or its delegated agent). Repeat the inspection specified in this paragraph at the earlier of the times specified in paragraphs (i)(1) and (i)(2) of this AD, and thereafter at intervals not to exceed 2,300 flight cycles or 4,600 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007. Accomplishment of Airbus Modification 05891H5128 terminates the repetitive inspections required by this paragraph.
(1) Within 3,000 flight cycles after doing the last inspection required by paragraph (i) of this AD.
(2) At the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Within 2,300 flight cycles or 4,600 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (i) of this AD.
(ii) Within 380 flight cycles or 770 flight hours, whichever occurs first, after the effective date of this AD.
Note 3: Airbus Service Bulletin A310-57-2020, Revision 07, dated June 5, 2006, is an additional source of guidance for accomplishing Airbus Modification 05891H5128.
For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, except airplanes on which Airbus modification 05026 has been embodied in production, or on which Airbus Service Bulletin A310-57-2005 has been done in service before the accumulation of 10,500 total flight cycles and 21,000 total flight hours: At the times specified in paragraph (k) of this AD, perform a detailed visual inspection to detect cracks around the bolts in the wing top skin upper surface of the front spar between rib 7 and rib 28, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996; or Airbus Mandatory Service Bulletin A310-57-2032, Revision 04, dated December 1, 2006. If any discrepancy is found, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or DGAC (or its delegated agent) or EASA (or its delegated agent). Except as required by paragraph (p) of this AD, repeat the detailed inspection specified in this paragraph at the earlier of the times specified in paragraphs (j)(1) and (j)(2) of this AD, and thereafter at intervals not to exceed 3,900 flight cycles or 7,900 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2032, Revision 04, dated December 1, 2006. Accomplishment of Airbus Modification 05026H0878 before the effective date of this AD terminates the repetitive inspection requirements of this paragraph; however, airplanes identified in paragraph (p) of this AD are applicable to the new inspections required by paragraph (p) of this AD. As of the effective date of this AD: Accomplishment of Airbus Modification 05026H0878 before the accumulation of 10,500 total flight cycles and 21,000 total flight hours terminates the repetitive inspection requirements of this paragraph.
(1) Within 4,500 flight cycles after doing the last inspection required by paragraph (j) of this AD.
(2) At the later of the times specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Within 3,900 flight cycles or 7,900 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (j) of this AD.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
Note 4: Airbus Service Bulletin A310-57-2005, Revision 03, dated October 2, 2006, is an additional source of guidance for accomplishing Airbus Modification 05026H0878.
Note 5: As of the effective date of this AD, if Airbus Service Bulletin A310-57-2005 is done on or after the accumulation of 10,500 total flight cycles or on or after the accumulation of 21,000 total flight hours, the actions specified in paragraph (j) of this AD are still required.
(k) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, except airplanes on which Airbus modification 05026 has been embodied in production, or on which Airbus Service Bulletin A310-57-2005 has been done in service before the accumulation of 10,500 total flight cycles and 21,000 total flight hours: At the earlier of the times specified in paragraphs (k)(1) and (k)(2) of this AD, do the detailed inspection required by paragraph (j) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later.
(2) At the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
(i) Prior to the accumulation of 10,500 total flight cycles or 21,000 total flight hours, whichever occurs first.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification 04987 has been done in production: At the compliance time specified in paragraph (m) of this AD, perform a high frequency eddy current (HFEC) or X-ray inspection to detect cracking of the stringer runouts inboard and outboard of rib 14 at stringers 6, 7, 8, and 9, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996; or Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006. Do the next inspection at the earlier of the times specified in paragraph (l)(1) and (l)(2) of this AD, and repeat the inspection thereafter at intervals not to exceed the applicable times specified in table 1 of this AD. If any crack is detected, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or DGAC (or its delegated agent) or EASA (or its delegated agent). As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006.
(1) Within the applicable interval specified in paragraph 1.B.(5) of Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996.
(2) At the later of the times specified in paragraph (l)(2)(i) and (l)(2)(ii) of this AD.
(i) Within the applicable interval specified in table 1 of this AD after doing the most recent inspection specified in paragraph (l) of this AD.
(ii) Within 1,100 flight cycles or 2,300 flight hours, whichever occurs first, after the effective date of this AD.
| Type of inspection | Repetitive interval (not to exceed) |
|---|---|
| X-Ray | 7,200 flight cycles or 14,500 flight hours, whichever occurs first. |
| HFEC | 9,400 flight cycles or 18,800 flight hours, whichever occurs first. |
(m) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification 04987 has been done in production: At the earlier of the times specified in paragraphs (m)(1) and (m)(2) of this AD, perform an inspection required by paragraph (l) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,500 flight cycles after January 20, 1999, whichever occurs later.
(2) At the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) Prior to the accumulation of 12,000 total flight cycles or 24,000 total flight hours, whichever occurs first.
(ii) Within 1,100 flight cycles or 2,300 flight hours after the effective date of this AD, whichever occurs first.
For Model A310-203 and A310-222 airplanes, on which Airbus Service Bulletin A310-57-2003 has been done in service on or after the accumulation of 9,400 total flight cycles or on or after the accumulation of 18,800 total flight hours: Do the inspection required by paragraph (g) of this AD at the later of the times specified in paragraphs (n)(1) and (n)(2) of this AD. Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 2,300 flight cycles or 4,700 flight hours, whichever occurs first.
(1) Within 2,300 flight cycles or 4,700 flight hours, whichever occurs first, after doing the most recent detailed inspection required by paragraph (g) of this AD.
(2) Within 1,500 flight cycles or 3,000 flight hours, after the effective date of this AD, whichever occurs first.
For Model A310-203, A310-204, A310-222, A310-304, A310-322, A310-324, and A310-325 airplanes, except for airplanes identified in paragraph (i) of this AD on which Airbus Modification 05891H5128 has not been done: At the applicable compliance time specified in table 2 of this AD, do the applicable actions specified in paragraph (o)(1) or (o)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007. If any cracking is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007; except where this service bulletin specifies to contact Airbus for repair, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent). Repeat the inspections thereafter at the applicable interval specified in table 2 of this AD. Certain compliance times specified in table 2 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours. For airplanes identified as Configuration 01 in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007, accomplishment of Airbus Modification 05891H5128 terminates the repetitive inspections required by this paragraph for Configuration 01 airplanes; thereafter do the applicable actions specified in paragraph (o)(2) of this AD at the times specified in table 2 of this AD.
Note 6: Airbus Service Bulletin A310-57-2020, Revision 07, dated June 5, 2006, is an additional source of guidance for accomplishing Airbus Modification 05891H5128.
(1) For Configuration 01 airplanes, as identified in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007: Do a rotating probe eddy current inspection for cracking in the holes around the overwing refueling aperture at ribs 13-14.
(2) For Configuration 02 through 06 airplanes, as identified in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007: Do an external detailed inspection for cracking of the top skin at ribs 13-14, and an internal detailed inspection for cracking of string 7 and string 8 of the overwing refuel aperture.
| Airplanes as Identified in Airbus Mandatory Service Bulletin A310-57-2006, revision 04, dated May 21, 2007 | Compliance time (whichever occurs later) | Repetitive interval (not to exceed) | |
| Configuration 01 airplanes | Prior to the accumulation of 6,000 total flight cycles | Within 380 flight cycles or 770 flight hours, whichever occurs first, after the effective date of this AD | 2,300 flight cycles or 4,600 flight hours, whichever occurs first. |
| Configuration 02 airplanes | Within 30,900 flight cycles or 61,900 flight hours, whichever occurs first, after accomplishing Airbus Service Bulletin A310-57-2020 | Within 1,500 flight cycles or 18 months, whichever occurs first, after the effective date of this AD | 11,300 flight cycles or 22,600 flight hours, whichever occurs first. |
| Configuration 03 airplanes | Within 30,900 flight cycles or 61,900 flight hours, whichever occurs first, after Airbus Modification 05891H5128 is done or Airbus Service Bulletin A310-57-2020 is accomplished | Within 1,500 flight cycles or 18 months, whichever occurs first, after the effective date of this AD | 12,000 flight cycles or 24,000 flight hours, whichever occurs first. |
| Configuration 04 and 05 short range airplanes | Before the accumulation of 25,900 total flight cycles or 72,500 total flight hours, whichever occurs first | Within 1,500 flight cycles or 18 months, whichever occurs first, after the effective date of this AD | 12,000 flight cycles or 33,600 flight hours, whichever occurs first. |
| Configuration 04 and 05 long range airplanes | Before the accumulation of 18,800 total flight cycles or 94,200 total flight hours, whichever occurs first | Within 1,500 flight cycles or 18 months, whichever occurs first, after the effective date of this AD | 9,400 flight cycles or 47,200 flight hours, whichever occurs first. |
| Configuration 06 | Before the accumulation of 30,900 total flight cycles or 61,900 total flight hours, whichever occurs first | Within 1,500 flight cycles or 18 months, whichever occurs first, after the effective date of this AD | 12,000 flight cycles or 24,000 flight hours, whichever occurs first. |
For Model A310-203 and A310-222 airplanes on which Airbus Service Bulletin A310-57-2005 has been done in service on or after the accumulation of 10,500 total flight cycles or on or after 21,000 total flight hours: Do the inspection required by paragraph (j) of this AD at the later of the times specified in paragraphs (p)(1) and (p)(2) of this AD. Repeat the inspection specified in paragraph (j) of this AD thereafter at intervals not to exceed 3,900 flight cycles or 7,900 flight hours, whichever occurs first.
(1) Within 3,900 flight cycles or 7,900 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (j) of this AD.
(2) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
For Model A310-203, A310-204, A310-222, A310-304, A310-322, and A310-324 airplanes, except airplanes on which Airbus modification 07601 has been done in production: Do the applicable actions specified in paragraphs (q)(1), (q)(2), and (q)(3) of this AD. If any cracking is found during any inspection, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent).
Note 7: For Model A310-304, A310-322, and A310-324 airplanes on which Airbus modification 07601 has been done, guidance for post-modification inspections can be found in Structure Significant Item (SSI) 57.21.16 of the Maintenance Review Board Document (MRBD).
(1) For airplanes on which Airbus Modification 07925H1113 and Modification 11578H5436 have not been done: At the applicable time specified in table 3 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 3 of this AD until Airbus Modification 07925H1113 or 11578H5436 has been done. After doing Airbus Modification 07925H1113 or 11578H5436 do the applicable actions specified in paragraph (q)(2) or (q)(3) of this AD at the times specified in paragraph (q)(2) or (q)(3) of this AD, as applicable. Certain compliance times specified in table 3 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
Note 8: Airbus Service Bulletin A310-57-2049, Revision 6, dated November 26, 1997, is an additional source of guidance for accomplishing Airbus Modification 07925H1113. Airbus Service Bulletin A310-57-2074, Revision 03, dated July 3, 2006, is an additional source of guidance for accomplishing Airbus Modification 11578H5436.
| Airplanes | Compliance time (whichever occurs later) | Repetitive interval (not to exceed) | |
| Model A310-203, A310-204, and A310-222 airplanes | Prior to the accumulation of 9,800 total flight cycles or 19,600 total flight hours, whichever occurs first | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 2,800 flight cycles or 5,700 flight hours, whichever occurs first. |
| Model A310-304, A310-322, and A310-324 short range airplanes | Prior to the accumulation of 7,100 total flight cycles or 20,100 total flight hours, whichever occurs first | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 2,400 flight cycles or 6,900 flight hours, whichever occurs first. |
| Model A310-304, A310-322, and A310-324 long range airplanes | Prior to the accumulation of 5,700 total flight cycles or 28,600 total flight hours, whichever occurs first | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 1,900 flight cycles or 9,800 flight hours, whichever occurs first. |
(2) For airplanes on which Airbus Modification 07925H1113 has been done: At the applicable time specified in table 4 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 4 of this AD. Certain compliance times specified in table 4 of this AD are applicable to short range use, AFT equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
| — | — | — | — |
|---|---|---|---|
| Airplanes | Compliance time (whichever occurs later) | Repetitive interval (not to exceed) | |
| Model A310-203, A310-204, and A310-222 airplanes | Prior to the accumulation of 14,700 total flight cycles or 29,400 total flight hours, whichever occurs first | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 9,400 flight cycles or 18,900 flight hours, whichever occurs first. |
| Model A310-304, A310-322, and A310-324 short range airplanes | Prior to the accumulation of 11,900 total flight cycles or 33,500 total flight hours, whichever occurs first | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 5,000 flight cycles or 14,000 flight hours, whichever occurs first. |
| Model A310-304, A310-322, and A310-324 long range airplanes | Prior to the accumulation of 9,500 total flight cycles or 47,700 total flight hours, whichever occurs first | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 4,000 flight cycles or 20,000 flight hours, whichever occurs first. |
(3) For airplanes on which Airbus Modification 11578H5436 has been done: At the applicable time specified in table 5 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 5 of this AD. Certain compliance times specified in table 5 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
| Airplanes | Compliance time (whichever occurs later) | Repetitive interval (not to exceed) | |
| Model A310-203, A310-204, and A310-222 airplanes | Within 29,600 flight cycles or 59,200 flight hours, whichever occurs first, after Airbus Modification 11578H5436 has been done | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 9,400 flight cycles or 18,900 flight hours, whichever occurs first. |
| Model A310-304, A310-322, and A310-324 short range airplanes | Within 24,200 flight cycles or 67,900 flight hours, whichever occurs first, after Airbus Modification 11578H5436 has been done | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 5,000 flight cycles or 14,000 flight hours, whichever occurs first. |
| Model A310-304, A310-322, and A310-324 long range airplanes | Within 19,300 flight cycles or 96,800 flight hours, whichever occurs first, after Airbus Modification 11578H5436 has been done | Within 750 flight cycles or 1,500 flight hours, whichever occurs first, after the effective date of this AD | 4,000 flight cycles or 20,000 flight hours, whichever occurs first. |
Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2038, Revision 03, dated September 4, 1998, are acceptable for compliance with the corresponding actions specified in paragraph (l) of this AD.
(s) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999, are acceptable for compliance with the corresponding actions specified in paragraph (q) of this AD.
Accomplishing an inspection in accordance with Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, or Revision 03, dated September 4, 1998; or Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006; terminates the requirements of paragraph (a) of AD 90-19-07.
Note 9: Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996; and Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006; are referred to in paragraph (l) of this AD. Airbus Service Bulletin A310-57-2038, Revision 03, dated September 4, 1998, is referred to in paragraph (r) of this AD.
Accomplishing an inspection in accordance with Airbus Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, as revised by Airbus Service Bulletin Change Notice 4A, dated October 16, 1996; Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999; or Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006; terminates the requirements of AD 91-06-18.
Note 10: Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006, is referred to in paragraph (q) of this AD. Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999, is referred to in paragraph (s) of this AD. Airbus Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, as revised by Airbus Service Bulletin Change Notice 4A, dated October 16, 1996, is referred to in paragraph (n) of AD 98-26-01.
Note 11: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (j) of this AD requires that you repair the crack(s) before further flight.
