AD 98-20-13 Airworthiness Directives; Airbus Model A300 Series Airplanes

Models named: A300 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A300 series airplanes, as listed in Airbus Industrie Service Bulletin A300-53-301, Revision 1, dated February 20, 1997; 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 (b) 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.

Required as indicated, unless accomplished previously. To detect and correct corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel, accomplish the following: (a) Within 18 months after the effective date of this AD, perform a visual inspection to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, between frames 55 to 58, and from stringers 13 to 31, left and right; in accordance with Airbus Industrie Service Bulletin A300-53- 301, dated September 28, 1995, or Revision 1, dated February 20, 1997. (1) If no corrosion is detected, repeat the inspection thereafter at intervals not to exceed 18 months on all areas on the fuselage skin panels that do not have a doubler installed or areas that have not been partially or completely replaced. (2) If any corrosion is detected, prior to further flight, accomplish rework and perform a residual thickness measurement, in accordance with the service bulletin. (i) If the measurement does not exceed the allowable limits specified by the Accomplishment Instructions of the service bulletin, repeat the inspection thereafter at intervals not to exceed 18 months. (ii) If the measurement does exceed the allowable limits specified by the Accomplishment Instructions of the service bulletin, prior to further flight, repair using a doubler, or replace the affected areas of the skin panel the installation of a new skin panel (partially or completely), in accordance [[Page 50487]] with the service bulletin. Accomplishment of either action constitutes terminating action for the repetitive inspections required by this AD for the repaired area or the replaced panel sections only. Note 2: Inspections, repairs, and replacements of the fuselage skin panels that surround the emergency exits immediately aft of the wing that have been accomplished prior to the effective date of this AD, in accordance with Airbus Industrie Service Bulletin A300-53- 301, dated September 28, 1995, are considered acceptable for compliance with the applicable action specified in this AD. (b) 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, 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, International Branch, ANM-116. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (c) 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. (d) The actions shall be done in accordance with Airbus Industrie Service Bulletin A300-53-301, dated September 28, 1995, or Airbus Industrie Service Bulletin A300-53-301, Revision 1, dated February 20, 1997. 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. Note 4: The subject of this AD is addressed in French airworthiness directive 97-357-231(B), dated November 19, 1997. (e) This amendment becomes effective on October 27, 1998. Issued in Renton, Washington, on September 14, 1998. Dorenda D. Baker, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-25031 Filed 9-21-98; 8:45 am] BILLING CODE 4910-13-P