Airworthiness Directive · Amendment 39-11790 · Airbus Industrie Model A300, A300-600, and A310 Series Airplanes
Airbus Industrie Model A300, A300-600, and A310 Series Airplanes
Superseded. A later AD replaced this one: AD 2014-23-13. Comply with the one in force.
The following airplanes, certificated in any category:
—Model A300 series airplanes, as listed in Airbus Service Bulletin A300-54-071, Revision 1, dated October 15, 1993.
—Model A300-600 series airplanes, as listed in Airbus Service Bulletin A300-54-6011, Revision 1, dated October 15, 1993.
—Model A310 series airplanes, as listed in Airbus Service Bulletin A310-54-2016, Revision 02, dated June 11, 1999.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, and A310 series airplanes, that currently requires inspections to detect cracks in the lower spar axis of the nacelle pylon between ribs 9 and 10, and repair, if necessary. The existing AD also provides for optional modification of the pylon, which terminates the inspections for Model A300 and A310 series airplanes and increases the threshold and repetitive interval of the inspections for Model A300-600 series airplanes. This amendment reduces the inspection threshold and requires repetitive inspections following accomplishment of the optional modification for Model A310 series airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
To prevent fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon, accomplish the following:
(a) 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), 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 Industrie Service Bulletin A300-54-071, dated November 12, 1991; or Revision 1, dated October 15, 1993.
(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 the service bulletin.
(3) If any crack is found that is greater than 30 mm, but less than 100 mm: Prior to the accumulation of 250 landings after crack discovery, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).
(4) If any crack is found that is greater than or equal to 100 mm: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
(5) Accomplishment of the modification specified in Airbus Industrie Service Bulletin A300-54-0079, dated October 15, 1993, constitutes terminating action for the inspections required by paragraph (a) of this AD.
(b) For Model A300-600 B4-620, C4-620, B4-622R, and B4-622 series airplanes: Except as provided by paragraph (b)(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), 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 Industrie Service Bulletin A300-54-6011, dated November 12, 1991, as amended by Service Bulletin Change Notice O.A., dated July 10, 1992; or Revision 1, dated October 15, 1993.
(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 the service bulletin.
(3) If any crack is found that is greater than 30 mm, but less than 100 mm: Prior to the accumulation of 250 landings after crack discovery, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).
(4) If any crack is found that is greater than or equal to 100 mm: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
(5) Accomplishment of the modification specified in Airbus Industrie Service Bulletin A300-54-6019, dated October 15, 1993, increases the threshold and repetitive interval of the inspections required by paragraph (b) of this AD to the threshold and interval specified in paragraph 2.D. of the Accomplishment Instructions of Airbus Industrie Service Bulletin A300-54-6011, Revision 1, dated October 15, 1993.
(c) 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 Industrie 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 (d) of this AD.
(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 the service bulletin.
(3) If any crack is found that is greater than 30 mm, but less than 100 mm: Prior to the accumulation of 250 landings after crack discovery, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
(4) If any crack is found that is greater than or equal to 100 mm: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
(5) Accomplishment of the modification specified in Airbus Industrie 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 (c) of this AD to the threshold and interval specified in paragraph 2.D. of the Accomplishment Instructions of Airbus Industrie Service Bulletin A310-54-2016, Revision 02, dated June 11, 1999.
(d) Perform the initial inspection required by paragraph (c) of this AD at the earlier of the times specified by paragraphs (d)(1) and (d)(2) of this AD.
(1) Prior to the accumulation of 25,000 total landings, or within 500 landings after June 12, 1995, whichever occurs later.
(2) At the applicable time specified by paragraph (d)(2)(i), (d)(2)(ii), or (d)(2)(iii) of this AD.
(i) For airplanes that have accumulated fewer than 10,000 landings as of the effective date of this AD: Perform the inspection prior to the accumulation of 3,800 total landings, or within 1,500 landings after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 10,000 total landings or more, but fewer than 20,000 total landings, as of the effective date of this AD: Perform the inspection within 1,000 landings after the effective date of this AD.
(iii) For airplanes that have accumulated 20,000 total landings or more as of the effective date of this AD: Perform the inspection within 500 landings after the effective date of this AD.
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.
