| AD Number | 97-01-11 | Status | Active |
| Effective Date | February 10, 1997 | Issue Date | Not specified |
| Docket Number | 92-NM-225-AD | Amendment | 39-9882 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Airbus SAS |
| Model(s) | A300 B2-1C A300 B2-203 A300 B2K-3C A300 B4-103 A300 B4-203 A300 B4-2C |
| Supersedes | 96-20-02 |
97-01-11 AIRBUS INDUSTRIE: Amendment 39-9882. Docket 92-NM-225-AD. Supersedes AD 96-20-02, amendment 39-9768.
Applicability: Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 series airplanes, on which Modification 2626 has not been installed; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
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 (f) 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 fatigue cracking, which could result in reduced structural integrity of the airplane, accomplish the following:
(a) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, and B4-103 series airplanes: Perform a detailed visual inspection to detect cracking of the fuselage, frame 47 at hole "I", in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992, at the times specified in paragraphs (a)(1) or (a)(2), as applicable.
(1) For Model A300 B2-1C, B2K-3C, and B2-203 series airplanes: Perform the inspection prior to the accumulation of 15,000 total landings, or within 50 landings after November 4, 1996 (the effective date of AD 96-20-02, amendment 39-9768), whichever occurs later.
(2) For Model A300 B4-2C and B4-103 series airplanes: Perform the inspection prior tothe accumulation of 18,700 total landings, or within 50 landings after November 4, 1996, whichever occurs later.
(b) For Model A300 B4-203 series airplanes: Prior to the accumulation of 14,100 total landings, or within 50 landings after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect cracking of the fuselage, frame 47 at hole "I", in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992.
(c) If no crack is detected during the inspection required by paragraph (a) or (b) of this AD, repeat the detailed visual inspection at intervals not to exceed 200 landings.
(d) If a crack is detected during any inspection required by paragraph (a), (b), or (c) of this AD, prior to further flight, repair in accordance with either paragraph (d)(1), (d)(2), or (d)(3) of this AD:
(1) Repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or
(2) Repair in accordance with crack repair procedures specified in Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992; or
(3) Repair in accordance with crack repair procedures specified in Airbus Service Bulletin A300-53-299, dated December 14, 1993.
(e) Conducting a repetitive Rototest inspection of hole "I" in accordance with Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992, or Airbus Service Bulletin A300-53-299, dated December 14, 1993, constitutes terminating action for the detailed visual inspections required by this AD. If any crack is found during a Rototest inspection, prior to further flight, repair it in accordance with that service bulletin.
(f) 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, FAA, Transport Airplane Directorate. 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.
(g) 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.
(h) The visual inspection shall be done in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of November 4, 1996 (61 FR 50988, September 30, 1996). 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.
(i) This amendment becomes effective on February 10, 1997.