AD 2004-01-03 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; except those on which Airbus Modification 27142 has been incorporated during production.

Required as indicated, unless accomplished previously. To prevent jamming of the locking pin of the passenger door, which could result in inability to open the passenger door and delay of evacuation in an emergency, resulting in possible injury to passengers or crew; accomplish the following: Restatement of Requirements of AD 98-01-12 Inspection/Corrective Action (a) Prior to the accumulation of 450 hours, time-in-service after one year from the delivery date of the airplane, or within 450 hours, time-in-service after February 17, 1998 (the effective date of AD 98-01-12, amendment 39-10275), whichever occurs later; perform an inspection to detect moisture or migrated bushings of the guide fittings of the upper safety locking pins on each passenger door, in accordance with Airbus Industrie All Operators Telex (AOT) 52-06, dated February 4, 1994. (1) If any moisture is found in the guide fitting, prior to further flight, remove the moisture, dry the guide fitting, fill it with low temperature grease, and reinstall the guide fitting with bolts, washers, and nuts in accordance with the AOT. (2) If any migrated bushing is found, prior to further flight, reinstall the bushing using Loctite 672 in accordance with the AOT. If the bushing cannot be reinstalled prior to further flight, the airplane may be operated without the upper locking pin for an additional 50 hours time-in-service or three days after accomplishing the inspection, whichever occurs first, provided that the requirements specified in paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of this AD are accomplished. This compliance time applies to each passenger door. (i) The connecting rod to the locking shaft shall be removed. (ii) The guide fitting shall remain installed. (iii) The cavity in the guide fitting (which results from the removal of the upper locking pin) shall be covered with high speed tape to prevent moisture ingress. Installation of Greasing Nipple (b) Within 15 months after February 17, 1998, install a greasing nipple on the guide fitting of the locking pin and on three telescopic rods on the passenger doors in accordance with Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994. New Requirements of This AD Modification (c) Modify the upper guide fitting of the locking pin in accordance with paragraphs 3.A. through 3.D. of the Accomplishment Instructions of Airbus Service Bulletin A320-52-1105, Revision 02, dated May 21, 2002; at the time specified in paragraph (c)(1) or (c)(2) of this AD, as applicable. Accomplishment of the modification before the effective date of this AD in accordance with Airbus Service Bulletin A320-52-1105, dated September 29, 2000; or Revision 01, dated August 7, 2001; is considered acceptable for compliance with the corresponding action in this paragraph. (1) For Model A320 and A321 series airplanes on which Airbus Service Bulletin A320-52-1057 has been incorporated in service: Within 1 year after the effective date of this AD. (2) For Model A319, A320, and A321 series airplanes on which Airbus Modification 24389 was done in production: Within 3 years after the effective date of this AD. Alternative Methods of Compliance (d)(1) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD. (2) Alternative methods of compliance, approved previously per AD 98-01-12, amendment 39-10275, are approved as alternative methods of compliance with paragraphs (a) and (b) of this AD, as applicable. Incorporation by Reference (e) The actions shall be done in accordance with Airbus Industrie All Operators Telex (AOT) 52-06, dated February 4, 1994; Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994; and Airbus Service Bulletin A320-52-1105, Revision 02, dated May 21, 2002; as applicable. (1) The incorporation by reference of Airbus Service Bulletin A320-52-1105, Revision 02, dated May 21, 2002, 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 Industrie All Operators Telex (AOT) 52-06, dated February 4, 1994; and Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994; was approved previously by the Director of the Federal Register as of February 17, 1998 (63 FR 1905, January 13, 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 2001-100(B), dated March 21, 2001. Effective Date (f) This amendment becomes effective on February 13, 2004. Issued in Renton, Washington, on December 29, 2003. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-123 Filed 1-8-04; 8:45 am] BILLING CODE 4910-13-P