Airworthiness Directive · Amendment 39-18029 · Nacelles/pylons
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category.
(1) Airbus Model A300 B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes on which Airbus Modification 2434 has been embodied in production.
(2) Airbus Model A300 airplane having manufacturer serial number 125, on the left hand side pylon only.
(3) Airbus Model A300 B4-620, B4-622R, and B4-622 airplanes, except for airplanes on which Airbus Modification 10149 has been embodied in production.
(4) Airbus Model A310-221, -222, -322, -324, and -325 airplanes, except for airplanes on which Airbus Modification 10149 has been embodied in production.
We are superseding Airworthiness Directive (AD) 2000-12-12, for certain Airbus Model A300, A300-600, and A310 series airplanes. AD 2000-12-12 required inspecting to detect cracks in the lower spar axis of the nacelle pylon between ribs 9 and 10, and repair if necessary. AD 2000-12-12 also provided for optional modification of the pylon, which terminated the inspections for Model A300 series airplanes. This new AD reduces the initial and repetitive inspection compliance times. This AD was prompted by reports of cracking of the lower pylon spar after accomplishing the existing modification. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the lower spar of the nacelle pylon.
This paragraph restates the requirements of paragraph (a) of AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with additional sources for repair approvals. For Model A300 B4-2C, B2K-3C, B2-203, B4-103, and B4-203 series airplanes: Prior to the accumulation of 9,000 total landings, or within 500 landings after June 12, 1995 (the effective date of AD 95-10-03, Amendment 39-9220 (60 FR 25604, May 12, 1995)), whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, in accordance with Airbus Service Bulletin A300-54-071, dated November 12, 1991; or Revision 1, dated October 15, 1993. Accomplishment of an inspection required by paragraph (k), (l), or (m) of this AD terminates the inspection requirements of this paragraph.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 2,500 landings.
(2) If any crack is found that is less than or equal to 30 millimeters (mm): Perform subsequent inspections and repair in accordance with the methods and times specified in Airbus Service Bulletin A300-54-071, dated November 12, 1991; or Revision 1, dated October 15, 1993.
(3) If any crack is found that is greater than 30 mm, but less than 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(4) If any crack is found that is greater than or equal to 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; or Airbus's EASA DOA.
(5) Accomplishment of the modification specified in Airbus Service Bulletin A300-54-0079, dated October 15, 1993, constitutes terminating action for the inspections required by paragraph (g) of this AD.
This paragraph restates the requirements of paragraph (b) of AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with additional sources for repair approvals. For Model A300-600, B4-620, C4-620, B4-622R, and B4-622 series airplanes: Except as provided by paragraph (h)(5) of this AD, prior to the accumulation of 4,000 total landings, or within 500 landings after June 12, 1995 (the effective date of AD 95-10-03, Amendment 39-9220 (60 FR 25604, May 12, 1995)), whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, in accordance with Airbus Service Bulletin A300-54-6011, dated November 12, 1991, as amended by Airbus Service Bulletin Change Notice O.A., dated July 10, 1992; or Revision 1, dated October 15, 1993. Accomplishment of an inspection required by paragraph (k), (l), or (m) of this AD terminates the inspection requirements of this paragraph.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 2,500 landings.
(2) If any crack is found that is less than or equal to 30 mm: Perform subsequent inspections and repair in accordance with the methods and times specified in Airbus Service Bulletin A300-54-6011, dated November 12, 1991, as amended by Airbus Service Bulletin Change Notice O.A., dated July 10, 1992; or Revision 1, dated October 15, 1993.
(3) If any crack is found that is greater than 30 mm, but less than 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; or Airbus's EASA DOA.
(4) If any crack is found that is greater than or equal to 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; or Airbus's EASA DOA.
(5) Accomplishment of the modification specified in Airbus Service Bulletin A300-54-6019, dated October 15, 1993, increases the threshold and repetitive interval of the inspections required by paragraph (h) of this AD to the threshold and interval specified in paragraph 2.D. of the Accomplishment Instructions of Airbus Service Bulletin A300-54-6011, Revision 1, dated October 15, 1993.
This paragraph restates the requirements of paragraph (c) of AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with additional sources for repair approvals. For Model A310-221, -222, -322, -324, and -325 series airplanes: Perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, in accordance with Airbus Service Bulletin A310-54-2016, dated November 12, 1991; or Revision 1, dated October 15, 1993; or Revision 02, dated June 11, 1999; at the time specified in paragraph (j) of this AD. Accomplishment of an inspection required by paragraph (k), (l), or (m) of this AD terminates the inspection requirements of this paragraph.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 2,500 landings.
(2) If any crack is found that is less than or equal to 30 mm: Perform subsequent inspections and repair in accordance with the methods and times specified in Airbus Service Bulletin A310-54-2016, dated November 12, 1991; or Revision 1, dated October 15, 1993; or Revision 02, dated June 11, 1999.
(3) If any crack is found that is greater than 30 mm, but less than 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; or Airbus's EASA DOA.
(4) If any crack is found that is greater than or equal to 100 mm: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent); or the EASA; or Airbus's EASA DOA.
(5) Accomplishment of the modification specified in Airbus Service Bulletin A310-54-2022, dated October 15, 1993; or Revision 01, dated March 16, 1999; increases the threshold and repetitive interval of the inspections required by paragraph (i) of this AD to the threshold and interval specified in paragraph 2.D. of the Accomplishment Instructions of Airbus Service Bulletin A310-54-2016, Revision 02, dated June 11, 1999.
This paragraph restates the requirements of paragraph (d) of AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000), with no changes. Perform the initial inspection required by paragraph (i) of this AD at the earlier of the times specified by paragraphs (j)(1) and (j)(2) of this AD.
(1) Prior to the accumulation of 25,000 total landings, or within 500 landings after June 12, 1995 (the effective date of AD 95-10-03, Amendment 39-9220 (60 FR 25604, May 12, 1995), whichever occurs later.
(2) At the applicable time specified by paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD.
(i) For airplanes that have accumulated fewer than 10,000 landings as of July 28, 2000 (the effective date of AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000)): Perform the inspection prior to the accumulation of 3,800 total landings, or within 1,500 landings after July 28, 2000, whichever occurs later.
(ii) For airplanes that have accumulated 10,000 total landings or more, but fewer than 20,000 total landings, as of July 28, 2000 (the effective date of AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000)): Perform the inspection within 1,000 landings after July 28, 2000.
(iii) For airplanes that have accumulated 20,000 total landings or more as of July 28, 2000 (the effective date of AD 2000-12-12, Amendment 39-11790 (65 FR 39072, June 23, 2000)): Perform the inspection within 500 landings after July 28, 2000.
(1) For airplanes identified in paragraph (k)(2) of this AD: Except as provided by paragraphs (n)(1) and (n)(4) of this AD, at the applicable compliance time specified in paragraph 1.E.(2), “Compliance,” of the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, or within 100 flight cycles after the effective date of this AD, whichever occurs later, do an eddy current inspection or liquid penetrant inspection for cracking of the lower spar of the pylon between ribs 9 and 10; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, except as required by paragraphs (n)(2) and (n)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the lower spar of the pylon between ribs 9 and 10 thereafter at intervals not to exceed the applicable interval specified in paragraph 1.E.(2), “Compliance,” of the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD. Accomplishment of corrective actions required by this paragraph terminates the repetitive inspections required by this paragraph. Accomplishment of an inspection required by this paragraph terminates the inspection requirements of paragraphs (g), (h), and (i) of this AD. Accomplishment of the optional modification specified in the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD terminates the repetitive inspections required by this paragraph.
(i) Airbus Service Bulletin A300-54-0071, Revision 04, dated April 11, 2013 (for Model A300 B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes).
(ii) Airbus Service Bulletin A310-54-2016, Revision 06, dated January 16, 2013 (for Model A310-221, -222, -322, -324, and -325 airplanes).
(iii) Airbus Service Bulletin A300-54-6011, Revision 03, dated June 23, 2011 (for Model A300 B4-620, B4-622R, and B4-622 airplanes).
(2) For airplanes that have not been modified or repaired with a doubler as specified in the applicable service bulletin specified in paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD, do the inspections required by paragraph (k)(1) of this AD.
(i) Airbus Service Bulletin A300-54-0079 (for Model A300 B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes).
(ii) Airbus Service Bulletin A310-54-2022 (for Model A310-221, -222, -322, -324, and -325 airplanes).
(iii) Airbus Service Bulletin A300-54-6019 (for Model A300 B4-620, B4-622R, and B4-622 airplanes).
For airplanes that have been repaired with a doubler as specified in the applicable Airbus service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD: At the applicable time specified in paragraph 1.E.(2), “Compliance,” in the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, except as specified in paragraphs (n)(1) and (n)(4) of this AD, do an eddy current inspection or liquid penetrant inspection for cracking of the lower spar of the pylon between ribs 9 and 10, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, except as required by paragraph (n)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the lower spar of the pylon between ribs 9 and 10 thereafter at intervals not to exceed the applicable interval specified in paragraph 1.E.(2), “Compliance,” of the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD. Accomplishment of an inspection required by this paragraph terminates the inspection requirements of paragraphs (g), (h), and (i) of this AD.
For airplanes that have been modified as specified in the applicable Airbus service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD: At the applicable time specified in paragraph 1.E.(2), “Compliance,” in the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, except as specified in paragraph (n)(1) and (n)(4) of this AD: Do an eddy current inspection or liquid penetrant inspection for cracking of the lower spar of the pylon between ribs 9 and 10; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD, except as required by paragraph (n)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the lower spar of the pylon between ribs 9 and 10 thereafter at intervals not to exceed the applicable interval specified in paragraph 1.E.(2), “Compliance,” of the applicable service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD. Accomplishment of an inspection required by this paragraph terminates the inspection requirements of paragraphs (g), (h), and (i) of this AD.
(1) Where the service bulletins specified in paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD specify a compliance time “from the publication date,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) If any crack is detected during any inspection required by paragraph (k), (l), or (m) of this AD, and the service bulletin specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD specifies to contact the manufacturer: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(3) Where the service bulletins specified in paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD specify to contact the manufacturer for inspection requirements: Inspect using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(4) Where the “Threshold” column in the tables in paragraph 1.E., “Compliance,” of the service bulletins specified in paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD specifies a compliance time in flight cycles/flight hours, this AD requires compliance within the corresponding time in total flight cycles/total flight hours; except that for tables for post-repair and post-modification airplanes, this AD requires compliance within the corresponding time after accomplishing the repair or modification.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
