Airworthiness Directive · Amendment 39-11742 · 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Superseded.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 2016-19-10. Comply with the one in force.
The following models, certificated in any category: Model A300 and A300-600 series airplanes, as listed in Airbus Service Bulletins A300-54-0073 and A300-54-6014, both Revision 1, dated March 28, 1994; and Model A310 series airplanes, except those on which Airbus Modification 10149 has been accomplished.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (m)(1) 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 Industrie Model A300, A300-600, and A310 series airplanes, that currently requires inspections to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, and repair, if necessary. For certain Model A310 series airplanes, this amendment reduces the currently required inspection thresholds and intervals, and removes an option for a terminating modification. 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 such fatigue cracking, which could result in reduced structural integrity of the engine pylon's lower spar, and possible separation of the engine from the airplane.
(a) For Model A300 series airplanes equipped with General Electric CF6-50C engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 10,900 total landings, or within 500 landings after June 28, 1996 (the effective date of AD 96-11-05, amendment 39-9630), whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 6,700 landings.
(2) If any crack is found that is less than 35 millimeters (1.38 inches), prior to further flight, stop-drill the crack in accordance with the procedures specified in Section 51-41-10 of the Structural Repair Manual (SRM). Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 17,900 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (a)(2) of this AD thereafter at intervals not to exceed 15,000 landings.
(ii) If any crack is found, prior to further flight, 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).
(3) If any crack is found that is greater than or equal to 35 mm (1.38 in.), 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).
(b) For Model A300 series airplanes equipped with General Electric CF6-50C engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 30,300 landings since installation of the modification, or within 500 landings after June 28, 1996, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 21,300 landings.
(2) If any crack is found, 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).
(c) For Model A300 series airplanes equipped with Pratt & Whitney JT9D-59A engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 8,600 total landings, or within 500 landings after June 28, 1996, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 5,700 landings.
(2) If any crack is found that is less than 35 mm (1.38 in.), prior to further flight, stop-drill the crack in accordance with the procedures specified in Section 51-41-10 of the SRM. Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 14,200 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (c)(2) of this AD thereafter at intervals not to exceed 12,800 landings.
(ii) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or by the DGAC (or its delegated agent).
(3) If any crack is found that is greater than or equal to 35 mm (1.38 in.), 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).
(d) For Model A300 series airplanes equipped with Pratt & Whitney JT9D-59A engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 24,000 landings since installation of the modification, or within 500 landings after June 28, 1996, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 18,200 landings.
(2) If any crack is found, 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).
(e) For Model A300-600 series airplanes equipped with General Electric CF6-80C2 engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 9,400 total landings, or within 500 landings after June 28, 1996, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 6,100 landings.
(2) If any crack is found that is less than or equal to 35 mm (1.38 in.), prior to further flight, stop-drill the crack in accordance with the procedures specified in Section 51-41-10 of the SRM. Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 15,600 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (e)(2) of this AD thereafter at intervals not to exceed 13,600 landings.
(ii) If any crack is found, 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).
(3) If any crack is found that is greater than or equal to 35 mm (1.38 in.), 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).
(f) For Model A300-600 series airplanes equipped with General Electric CF6-80C2 engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 26,400 landings since installation of the modification, or within 500 landings after June 28, 1996, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 19,400 landings.
(2) If any crack is found, 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).
(g) For Model A300-600 series airplanes equipped with Pratt & Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 5,700 total landings, or within 500 landings after June 28, 1996, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 4,400 landings.
(2) If any crack is found that is less than 35 mm (1.38 in.), prior to further flight, stop-drill the crack in accordance with the procedures specified in Section 51-41-10 of the SRM. Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 10,100 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (g)(2) of this AD thereafter at intervals not to exceed 10,000 landings.
(ii) If any crack is found, 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).
(3) If any crack is found that is greater than or equal to 35 mm (1.38 in.), 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).
(h) For Model A300-600 series airplanes equipped with Pratt & Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 17,000 landings since installation of the modification, or within 500 landings after June 28, 1996, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 14,500 landings.
(2) If any crack is found, 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).
(i) For Model A310 series airplanes on which the modification specified in Airbus Service Bulletin A310-54-2023, dated October 15, 1993, has not been accomplished: Perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A310-54-2017, Revision 03, dated June 11, 1999, at the applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD.
(1) For airplanes that have accumulated fewer than 10,000 total landings as of the effective date of this AD: Inspect prior to the accumulation of 7,000 total landings, or within 1,500 landings after the effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 10,000 total landings or more and fewer than 20,000 total landings as of the effective date of this AD: Inspect within 1,000 landings after the effective date of this AD.
(3) For airplanes that have accumulated 20,000 total landings or more as of the effective date of this AD: Inspect within 500 landings after the effective date of this AD.
(j) If no crack is found during the inspection required by paragraph (i) of this AD, accomplish the actions specified by either paragraph (j)(1) or (j)(2) of this AD.
(1) Repeat the inspection thereafter at intervals not to exceed 6,400 landings. Or
(2) Prior to further flight, modify the lower spar between ribs 6 and 7 in accordance with Airbus Industrie Service Bulletin A310-54-2023, dated October 15, 1993, and thereafter accomplish the actions required by paragraph (l) of this AD.
(k) If any crack is found during any inspection required by paragraph (i) or (j) of this AD, accomplish the actions required by paragraph (k)(1) or (k)(2) of this AD, as applicable.
(1) If the crack is less than 35 mm (1.38 in.), prior to further flight, repair in accordance with Airbus Industrie Service Bulletin A310-54-2017, Revision 03, dated June 11, 1999. Thereafter, within 13,600 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair, and on the fasteners located at the end of the doubler, in accordance with the service bulletin.
(i) If no crack is found during the inspection required by paragraph (k)(1) of this AD, repeat the inspection required by paragraph (i) of this AD thereafter at intervals not to exceed 11,600 landings.
(ii) If any crack is found during the inspection required by paragraph (k)(1) of this AD, 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).
(2) If the crack is equal to or greater than 35 mm (1.38 in.), 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).
(l) For Model A310 series airplanes on which the modification specified in Airbus Industrie Service Bulletin A310-54-2023, dated October 15, 1993, has been accomplished: Within 23,000 landings after accomplishment of the modification, or within 90 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A310-54-2017, Revision 03, dated June 11, 1999.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 15,500 landings.
(2) If any crack is found during any inspection required by paragraph (l) or (l)(1) of this AD, 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).
(m)(1) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.
(2) Alternate methods of compliance approved previously in accordance with AD 96-11-05, Amendment 39-9630, for paragraphs (a) through (h) of that AD, are approved as alternative methods of compliance with paragraphs (a) through (h) of this AD.
Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.
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.
