96-11-05 AIRBUS INDUSTRIE: Amendment 39-9630. Docket 95-NM-85-AD.
Applicability: Model A300, A300-600, and A310 series airplanes; as listed in Airbus Industrie Service Bulletins A300-54-0073, A300-54-6014, and A310-54-2017, all Revision 1, all dated March 28, 1994; certificated in any category.
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 (k) 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.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the lower spar, accomplish the following:
(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 the effective date of this AD, 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 mm, prior to further flight, stop- drill thecrack 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(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 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 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, Standardization Branch, ANM-113.
(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 the effective date of this AD, 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, 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, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(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 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 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, Standardization Branch, ANM-113.
(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 the effective date of this AD, whichever occurslater, 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, 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, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(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 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 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, Standardization Branch, ANM-113.
(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 the effective date of this AD, 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, 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, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(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 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 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, StandardizationBranch, ANM-113.
(i) For Model A310 series airplanes equipped with General Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney PW4000 engines: Prior to the accumulation of 36,700 total landings, or within 500 landings after the effective date of this AD, 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 A310-54-2017, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 15,000 landings.
(2) If any crack is found that is less than 35 mm, 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 40,000 landings after accomplishing therepair, 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 (i)(2) of this AD thereafter at intervals not to exceed 33,000 landings.
(ii) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(j) For Model A310 series airplanes equipped with General Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney PW4000 engines: Accomplishment of the modification specified in Airbus Industrie Service Bulletin A310-54-2023, dated October 15, 1993, constitutes terminating action for the inspections required by paragraph (i) of this AD.
(k) 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, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(l) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
(m) The actions shall be done in accordance with the following Airbus Industrie service bulletins, whichcontain the specified effective pages:
Service Bulletin
Referenced and Date
Revision Level
Page Number
Date
Shown on Page
Shown on Page
A300-54-0073,
Revision 1,
March 28, 1994
1, 5
2-4, 6-36
1
Original
March 28, 1994
October 15, 1993
A300-54-6014,
Revision 1,
March 28, 1994
1-4, 13
5-12, 14-44
1
Original
March 28, 1994
October 15, 1993
A310-54-2017,
Revision 1,
March 28, 1994
1, 5
2-4, 6-48
1
Original
March 28, 1994
October 15, 1993
A310-54-2023,
October 15, 1993
1-38
Original
October 15, 1993
This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(n) This amendment becomes effective on June 28, 1996.