Airworthiness directives › 2004-07-15
AD 2004-07-15 Airworthiness Directives; Airbus Model A321-111, -112, and -131 Series Airplanes
Models named: A321-111, -112, -131 series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model A321-111, -112, and -131 series airplanes; except those on which Airbus Modification 24977 has been accomplished during production, or on which Airbus Modification 26010 has been accomplished; certificated in any category.
Compliance
Required as indicated, unless accomplished previously. To detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane, accomplish the following: Requirements of AD 98-25-05 Repetitive Inspections and Corrective Actions (a) Prior to the accumulation of 20,000 total flight cycles, or within 120 days after December 18, 1998 (the effective date of AD 98-25-05, amendment 39-10928), whichever occurs later, perform an ultrasonic inspection to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar, in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, dated October 25, 2001. (1) If no cracking is detected, prior to further flight, repair the sealant in the inspected areas and repeat the ultrasonic inspections thereafter at intervals not to exceed 7,700 flight cycles, until paragraph (b) or (d) of this AD is accomplished. (2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent). Optional Terminating Action (b) Accomplishment of visual and eddy current inspections to detect cracking in the area surrounding certain attachment holes of the forward pintle fittings of the MLG and the actuating cylinder anchorage fittings on the inner rear spar; follow-on corrective actions, as applicable; and rework of the attachment holes; in accordance with Airbus Service Bulletin A320-57-1100, dated July 28, 1997, constitutes terminating action for the repetitive inspection requirements of this AD. If any cracking is detected during accomplishment of any inspection described in the service bulletin, and the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, or the DGAC (or its delegated agent). New Requirements of This AD Repetitive Inspections for Airplanes Not Previously Inspected Per Paragraph (a) (c) For airplanes on which the initial inspection required by paragraph (a) of this AD has not been accomplished as of the effective date of this AD: Accomplish the inspection required by paragraph (a) of this AD, at the earlier of the times specified in paragraphs (c)(1) and (c)(2) of this AD. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (b) of this AD is accomplished. Accomplishment of this paragraph eliminates the need to accomplish repetitive inspections at the intervals required by paragraph (a)(1) of this AD. (1) Prior to the accumulation of 20,000 total flight cycles. (2) Prior to the accumulation of 37,300 total flight hours, or within 120 days after the effective date of this AD, whichever occurs later. Repetitive Inspections for Airplanes Previously Inspected Per Paragraph (a) (d) For airplanes on which the initial inspection required by paragraph (a) of this AD has been accomplished as of the effective date of this AD, and no cracking was found: Do the next inspection at the earlier of the times specified in paragraphs (d)(1) or (d)(2) of this AD, and repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (b) of this AD is accomplished. Accomplishment of this paragraph terminates the repetitive inspections required by paragraph (a)(1) of this AD. (1) Within 7,700 flight cycles since the most recent inspection. (2) At the later of the times specified in paragraph (d)(2)(i) or (d)(2)(ii) of this AD: (i) Within 5,500 flight cycles or 10,200 flight hours since the most recent inspection, whichever occurs first. (ii) Within 120 days after the effective date of this AD. Repair (e) If any cracking is detected during any inspection required by paragraph (c) or (d) of this AD: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent). No Reporting Requirement (f) Although Airbus Service Bulletin A320-57-1101, Revision 02, dated October 25, 2001, specifies to submit certain information to the manufacturer, this AD does not include such a requirement. Alternative Methods of Compliance (g) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (h) Unless otherwise provided by this AD, the actions shall be done in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or Airbus Service Bulletin A320-57-1101, Revision 02, dated October 25, 2001. (1) The incorporation by reference of Airbus Service Bulletin A320-57-1101, Revision 02, dated October 25, 2001; is approved by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of Airbus Service Bulletin A320-57-1101, dated July 24, 1997; was approved previously by the Director of the Federal Register as of December 18, 1998 (63 FR 66753, December 3, 1998). (3) Copies may be obtained from Airbus, 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 1: The subject of this AD is addressed in French airworthiness directive 2001-633(B), dated December 26, 2001. Effective Date (h) This amendment becomes effective on April 21, 2004. Issued in Renton, Washington, on March 25, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-7354 Filed 4-5-04; 8:45 am] BILLING CODE 4910-13-P
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