AD 99-06-10 Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes

Models named: A300, A300-600 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A300 and A300-600 series airplanes on which Airbus Modification 11523 (reference Airbus Service Bulletins A300- 53-0331 and A300-53-6107, both dated March 18, 1997) has not been accomplished, or on which Airbus Modification 11522 has not been installed in production; certificated in any category. 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 (c) 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 prevent failure of the rivets that attach the pressurized floor panel to gantries 4 and 5, which could result in the loss of the floor panel and consequent rapid decompression of the airplane, accomplish the following: (a) Accomplish paragraph (a)(1), or paragraphs (a)(2) and (a)(3), of this AD at the times specified in those paragraphs in accordance with Airbus Service Bulletin A300-53-0331, Revision 01 (for Airbus Model A300 series airplanes); or A300-53-6107, Revision 01 (for Airbus Model A300-600 series airplanes), both dated November 5, 1998; as applicable. (1) Replace the rivets that attach the pressurized floor panel to gantries 4 and 5 with new titanium alloy bolts, at the applicable time specified in paragraph (a)(1)(i), (a)(1)(ii), (a)(1)(iii), or (a)(1)(iv) of this AD. (i) For Airbus Model A300-600 series airplanes, replace the rivets prior to the accumulation of 7,150 total flight cycles. (ii) For Airbus Model A300 B4-203 series airplanes, replace the rivets prior to the accumulation of 10,000 total flight cycles. (iii) For Airbus Model A300 B4-2C and B4-103 series airplanes, replace the rivets prior to the accumulation of 12,300 total flight cycles. [[Page 12244]] (iv) For Airbus Model A300 B2-1C, B2-203, and B2K-3C series airplanes, replace the rivets prior to the accumulation of 14,600 total flight cycles. (2) Perform a detailed visual inspection to detect any broken or discrepant rivets that attach the pressurized floor panel to gantries 4 and 5, at the applicable time specified in paragraph (a)(2)(i), (a)(2)(ii), (a)(2)(iii), or (a)(2)(iv) of this AD. Repeat the inspection thereafter at intervals not to exceed 350 flight cycles until accomplishment of the action required by paragraph (a)(3) of this AD. (i) For Airbus Model A300-600 series airplanes, inspect the rivets prior to the accumulation of 7,500 total flight cycles, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (ii) For Airbus Model A300 B4-203 series airplanes, inspect the rivets prior to the accumulation of 10,350 total flight cycles, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (iii) For Airbus Model A300 B4-2C and B4-103 series airplanes, inspect the rivets prior to the accumulation of 12,650 total flight cycles, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (iv) For Airbus Model A300 B2-1C, B2-203, and B2K-3C series airplanes, inspect the rivets prior to the accumulation of 14,950 total flight cycles, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (3) Within 3,000 flight cycles after the effective date of this AD, replace the rivets that attach the pressurized floor panel to gantries 4 and 5 with new titanium alloy bolts in accordance with the applicable service bulletin. Accomplishment of this replacement constitutes terminating action for the repetitive inspections. (b) If any discrepant or broken rivet is detected during any inspection specified in paragraph (a)(2) of this AD, prior to further flight, accomplish either paragraph (b)(1) or (b)(2) of this AD, as applicable, in accordance with Airbus Service Bulletin A300- 53-0331, Revision 01 (for Airbus Model A300 series airplanes); or A300-53-6107, Revision 01 (for Airbus Model A300-600 series airplanes), both dated November 5, 1998; as applicable. (1) If less than 15 discrepant or broken rivets are detected, prior to further flight, replace the discrepant or broken rivets with serviceable rivets and continue the repetitive inspections, in accordance with the applicable service bulletin, until accomplishment of the action required by paragraph (a)(3) of this AD. (2) If 15 or more discrepant or broken rivets are detected, prior to further flight, replace all the rivets that attach the pressurized floor panel to gantries 4 and 5 with new titanium alloy bolts, in accordance with the applicable service bulletin. Accomplishment of this replacement constitutes terminating action for the repetitive inspections required by this AD. Note 2: Accomplishment of the actions required by paragraphs (a) and (b) of this AD in accordance with Airbus Service Bulletin A300- 53-0331, dated March 18, 1997 (for Airbus Model A300 series airplanes); or Airbus Service Bulletin A300-53-6107, dated March 18, 1997 (for Airbus Model A300-600 series airplanes), prior to the effective date of this AD, is acceptable for compliance with those paragraphs. (c) 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. (d) 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. (e) The actions shall be done in accordance with Airbus Service Bulletin A300-53-0331, Revision 01, dated November 5, 1998, or Airbus Service Bulletin A300-53-6107, Revision 01, dated November 5, 1998. 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 97-176-229(B), dated August 13, 1997. (f) This amendment becomes effective on April 16, 1999. Issued in Renton, Washington, on March 4, 1999. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-5993 Filed 3-11-99; 8:45 am] BILLING CODE 4910-13-P