AD 2002-03-11 Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes

Models named: A319, A320, A321 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A319, A320, and A321 series airplanes; certificated in any category; as listed in Airbus Service Bulletin A320-55A1027, dated May 13, 2000, Revision 01, dated August 1, 2000, or Revision 02, dated February 13, 2001; except those airplanes on which Airbus Service Bulletin A320-55-1028, Revision 02, dated July 26, 2000, Revision 03, dated November 2, 2000, or Revision 04, dated April 13, 2001; has been accomplished. 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 (g)(1) 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 bonds of the vertical stabilizer spar box to the skin, which could lead to reduced structural integrity of the spar boxes, accomplish the following: Restatement of Requirements of AD 2000-11-27 Ultrasonic Inspection (a) Within 60 days after June 28, 2000 (the effective date of AD 2000-11-27, amendment 39-11776): Perform a one-time ultrasonic inspection to detect disbonding (damage) of the skin attachments at the stringers and spars of the vertical stabilizer, left- and right-hand sides, in accordance with Airbus Service Bulletin A320-55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; or Revision 02, dated February 13, 2001. Modification (for Certain Airplanes) (b) For airplanes with manufacturer's serial numbers listed in paragraph B of the Planning Information of Airbus Service Bulletin A320-55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; or Revision 02, dated February 13, 2001: Prior to or concurrent with the ultrasonic inspection required by paragraph (a) of this AD, modify the vertical stabilizer to ensure proper reinforcement of the structure/skin attachments, in accordance with Airbus Service Bulletin A320-55-1026, Revision 01, dated May 20, 1999. New Requirements of This AD Repetitive Inspections and Repair, If Necessary (c) Within 1,100 flight cycles from the previous inspection performed in accordance with paragraph (a) of this AD, or 60 days after the effective date of this AD, whichever occurs later: Perform an ultrasonic inspection to detect disbonding of the skin attachment at the spars and the stringers of the vertical stabilizer spar box, in accordance with Airbus Service Bulletin A320-55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; or Revision 02, dated February 13, 2001. (d) If no damage is detected, or if only a single area of damage is found and it is less than or equal to an area of 300 square millimeters (mm 2 ) during any ultrasonic inspection required by this AD, repeat the ultrasonic inspection thereafter at intervals not to exceed 1,100 flight cycles. (e) If any damage is detected and the area of damage found is greater than 300 mm 2 , or if multiple areas of damage are found on one specific component (stringer/spar attachment) during any ultrasonic inspection required by this AD, prior to further flight, accomplish applicable repairs in accordance with Airbus Service Bulletin A320-55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; or Revision 02, dated February 13, 2001. Repeat the ultrasonic inspection thereafter at intervals not to exceed 1,100 flight cycles. Modification (f) Within 5 years after the date of manufacture of the airplane: Install fasteners to reinforce the attachment between the skin panel and areas of the vertical stabilizer affected by disbonding, in accordance with Airbus Service Bulletin A320-55-1028, Revision 04, dated April 13, 2001. Accomplishment of the installation terminates the repetitive inspections required by paragraph (c) of this AD. Note 2: Installations accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-55-1028, Revision 02, dated July 26, 2000, or Revision 03, dated November 2, 2000, are considered acceptable for compliance with paragraph (f) of this AD. Alternative Methods of Compliance (g)(1) 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. (2) Alternative methods of compliance, approved previously in accordance with AD 2000-11-27, amendment 39-11776, are approved as alternative methods of compliance with paragraphs (a) and (b) of this AD. 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. Special Flight Permits (h) Special flight permits may be issued in accordance with §§ 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. Incorporation by Reference (i) The actions shall be done in accordance with Airbus Service Bulletin A320-55-1026, Revision 01, dated May 20, 1999; Airbus Service Bulletin A320-55A1027, dated May 13, 2000, Airbus Service Bulletin A320-55A1027, Revision 01, dated August 1, 2000, or Airbus Service Bulletin A320-55A1027, Revision 02, dated February 13, 2001; and Airbus Service Bulletin A320-55-1028, Revision 04, dated April 13, 2001. (1) The incorporation by reference of Airbus Service Bulletin A320-55A1027, Revision 01, dated August 1, 2000; Airbus Service Bulletin A320-55A1027, Revision 02, dated February 13, 2001; and Airbus Service Bulletin A320-55-1028, Revision 04, dated April 13, 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 A320-55-1026, Revision 01, dated May 20, 1999; and Airbus Service Bulletin A320-55A1027, dated May 13, 2000; was approved previously by the Director of the Federal Register as of June 28, 2000 (65 FR 37029, June 13, 2000). (3) 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 2000-520-159(B), dated December 13, 2000. Effective Date (j) This amendment becomes effective on March 19, 2002. Issued in Renton, Washington, on February 7, 2002. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-3455 Filed 2-11-02; 8:45 am] BILLING CODE 4910-13-P