AD 98-21-34 Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

Models named: A300, A310, A300-600 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model A300, A310, and A300-600 series airplanes; 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 (d) 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 and cracks on the bottom wing skin area, which could result in reduced structural integrity of the airplane, accomplish the following: (a) At the time specified in paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as applicable: Except as required by paragraphs (b) and (c) of this AD, perform an inspection for corrosion and cracks on the bottom wing skin area, and accomplish follow-on corrective actions, in accordance with Airbus Service Bulletin A300-57-0204, dated December 4, 1995 (for Model A300 series airplanes); A310-57-2061, dated December 4, 1995 (for Model A310 series airplanes); or A300-57-6047, Revision 01, dated October 16, 1996, as revised by Change Notice 1.A., dated February 24, 1997 (for Model A300-600 series airplanes); as applicable; subsequently referred to in this AD as the ``applicable'' service bulletins. Thereafter, repeat the inspection at intervals not to exceed 5 years. (1) For airplanes with 5 years or less since date of manufacture: Prior to the accumulation of 5 years since date of manufacture or within 18 months after the effective date of this AD, whichever occurs later. (2) For airplanes with more than 5 years, but less than 15 years since date of manufacture: Within 18 months after the effective date of this AD. (3) For airplanes with more than 15 years, but less than 20 years since date of manufacture: Within 12 months after the effective date of this AD. (4) For airplanes with more than 20 years since date of manufacture: Within 6 months after the effective date of this AD. (b) If any corrosion or crack is found during an inspection required by paragraph (a) of this AD, and the applicable service bulletin specifies to contact Airbus for an appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (c) If any crack is found during an inspection required by paragraph (a) of this AD, and the applicable service bulletin specifies to refer to Table B, Figure 4, of the service bulletin to determine the fatigue inspection threshold and interval: Use Table 1, 2, 3, 4, or 5, of this AD, as applicable, to determine the fatigue inspection threshold and interval in flight cycles (FC) or flight hours (FH). Table 1.--Airbus Service Bulletin A300-57-204 (Model A300 B2) Fatigue Inspection ---------------------------------------------------------------------------------------------------------------- Detailed visual NDT (HFEC) Interval (FC Area Threshold (FC or FH, interval (FC or FH, or FH, whichever occurs whichever occurs first) whichever occurs first) first) ---------------------------------------------------------------------------------------------------------------- 1, 2, 3a \1\......................... 10,400 FC or 15,800 FH. 10,400 FC or 15,800 FH. 10,400 FC or 15,800 FH. 3b, 4a \2\........................... 7,200 FC or 11,000 FH.. 2,500 FC or 3,800 FH... 6,300 FC or 9,600 FH. 4b................................... 10,400 FC or 15,800 FH. 10,400 FC or 15,800 FH. 10,400 FC or 15,800 FH. 5, 6................................. 9,900 FC or 15,100 FH.. 8,700 FC or 13,200 FH.. 9,900 FC or 15,100 FH. 7, 8................................. 6,600 FC or 10,000 FH.. 5,000 FC or 7,700 FH... 6,400 FC or 9,700 FH. ---------------------------------------------------------------------------------------------------------------- \1\ Area 3, as defined by Table B, Table 4, of SB A300-57-0204, has been split into areas 3a and 3b with a borderline between stiffener 43.2 and lattice flange 44 for Tables 1, 2, and 3 of this AD. \2\ Area 4, as defined by Table B, Table 4, of SB A300-57-0204, has been split into areas 4a and 4b with a borderline between lattice flange 44 for stiffener 44.1 for Tables 1, 2, and 3 of this AD. Table 2.--Airbus Service Bulletin A300-57-204 (Model A300 B4-100) Fatigue Inspection ---------------------------------------------------------------------------------------------------------------- Detailed visual NDT (HFEC) interval (FC Area Threshold (FC or FH, interval (FC or FH, or FH, whichever occurs whichever occurs first) whichever occurs first) first) ---------------------------------------------------------------------------------------------------------------- 1, 2, 3a............................. 9,500 FC or 15,600 FH.. 8,600 FC or 14,200 FH.. 9,500 FC or 15,600 FH. 3b, 4a............................... 6,700 FC or 12,000 FH.. 2,000 FC or 3,300 FH... 5,000 FC or 8,200 FH. 4b................................... 9,500 FC or 15,600 FH.. 8,600 FC or 14,200 FH.. 9,500 FC or 15,600 FH. 5, 6................................. 8,200 FC or 13,400 FH.. 7,200 FC or 11,900 FH.. 8,200 FC or 13,400 FH. 7, 8................................. 4,600 FC or 7,600 FH... 3,600 FC or 5,900 FH... 4,500 FC or 7,400 FH. ---------------------------------------------------------------------------------------------------------------- Table 3.--Airbus Service Bulletin A300-57-204 (Model A300 B4-100) Fatigue Inspection ---------------------------------------------------------------------------------------------------------------- Detailed visual NDT (HFEC) interval (FC Area Threshold (FC or FH, interval (FC or FH, or FH, whichever occurs whichever occurs first) whichever occurs first) first) ---------------------------------------------------------------------------------------------------------------- 1, 2, 3a............................. 9,900 FC or 21,600 FH.. 9,000 FC or 19,200 FH.. 9,900 FC or 21,100 FH. 3b, 4a............................... 7,000 FC or 14,900 FH.. 2,100 FC or 4,500 FH... 5,200 FC or 11,100 FH. 4b................................... 9,900 FC or 21,100 FH.. 9,000 FC or 19,200 FH.. 9,900 FC or 21,100 FH. 5, 6................................. 8,500 FC or 18,100 FH.. 7,500 FC or 16,000 FH.. 8,500 FC or 18,100 FH. 7, 8................................. 4,800 FC or 10,200 FH.. 3,700 FC or 7,900 FH... 4,700 FC or 10,000 FH. ---------------------------------------------------------------------------------------------------------------- [[Page 55526]] Table 4.--Airbus Service Bulletin A330-57-2061 (Model A310 and A310-300) Fatigue Inspection ---------------------------------------------------------------------------------------------------------------- Detailed visual NDT (HFEC) interval (FC Area Threshold (FC or FH, interval (FC or FH, or FH, whichever occurs whichever occurs first) whichever occurs first) first) ---------------------------------------------------------------------------------------------------------------- 1.................................... 12,800 FC or 36,600 FH. 10,500 FC or 29,900 FH. 12,800 FC or 36,600 FH. 2.................................... 5,700 FC or 16,300 FH.. 4,600 FC or 13,100 FH.. 5,700 FC or 16,300 FH. 3, 5................................. 5,100 FC or 14,700 FH.. 4,100 FC or 11,800 FH.. 5,100 FC or 14,700 FH. 4.................................... 4,500 FC or 12,800 FH.. 1,800 FC or 5,100 FH... 4,500 FC or 12,800 FH. 6.................................... 19,400 FC or 55,300 FH. 16,500 FC or 47,000 FH. 19,400 FC or 55,300 FH. 7.................................... 16,300 FC or 46,500 FH. 13,800 FC or 39,500 FH. 16,300 FC or 46,500 FH. ---------------------------------------------------------------------------------------------------------------- Table 5.--Airbus Service Bulletin A300-57-6047 (Model A300-600) Fatigue Inspection ---------------------------------------------------------------------------------------------------------------- Detailed visual NDT (HFEC) interval (FC Area Threshold (FC or FH, interval (FC or FH, or FH, whichever occurs whichever occurs first) whichever occurs first) first) ---------------------------------------------------------------------------------------------------------------- 1, 2................................. 13,600 FC or 42,900 FH. 11,800 FC or 37,000 FH. 15,500 FC or 48,800 FH. 3.................................... 6,500 FC or 20,400 FH.. 5,800 FC or 18,400 FH.. 6,900 FC or 21,600 FH. 4, 6................................. 4,800 FC or 15,100 FH.. 4,500 FC or 14,200 FH.. 5,000 FC or 15,700 FH 5.................................... 2,100 FC or 6,500 FH... 900 FC or 3,000 FH..... 2,100 FC or 6,500 FH. 7.................................... 5,700 FC or 18,100 FH.. 5,500 FC or 17,200 FH.. 6,300 FC or 19,800 FH. 8.................................... 2,400 FC or 7,400 FH... 2,100 FC or 6,500 FH... 2,400 FC or 7,400 FH. ---------------------------------------------------------------------------------------------------------------- (d) 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. 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. (e) 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. (f) Except as provided by paragraphs (b) and (c) of this AD, the actions shall be done in accordance with the following Airbus service bulletins, as applicable, which contain the specified effective pages: ---------------------------------------------------------------------------------------------------------------- Service bulletin referenced and Revision level shown date Page No. on page Date shown on page ---------------------------------------------------------------------------------------------------------------- A300-57-0204, December 4, 1995.... 1-101................ Original............ December 4, 1995. A310-57-2061, December 4, 1995.... 1-111................ Original............ December 4, 1995. A300-57-6047, October 16, 1996.... 1-3, 29, 30.......... 01.................. October 16, 1996. 4-29, 31-65.......... Original............ January 4, 1996. Change Notice 1.A., February 24, 1, 2................. Original............ February 24, 1997. 1997, for Airbus Service Bulletin A300-57-6047, October 16, 1996. ---------------------------------------------------------------------------------------------------------------- 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 3: The subject of this AD is addressed in French airworthiness directive 97-006-210(B), dated January 2, 1997. (g) This amendment becomes effective on November 20, 1998. Issued in Renton, Washington, on October 7, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-27479 Filed 10-15-98; 8:45 am] BILLING CODE 4910-13-P