AD 2001-08-06 Airworthiness Directives; Airbus Model A300 B4-620, A310-203, A310-221, and A310-222 Series Airplanes

Models named: A300 B4-620, A310-203, A310-221, A310-222 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A300 B4-620, A310-203, A310-221, and A310-222 series airplanes; certificated in any category; as listed in Airbus Service Bulletin A300-53-6120 or A310-53-2109, both dated May 5, 2000; excluding airplanes on which Airbus Modification 3632 has been accomplished. 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 detect and correct fatigue cracking of fuselage frame 07 in the upper frame section assembly of the lateral cockpit windows, which could result in reduced structural integrity of the airplane, accomplish the following: Inspection and Corrective Actions (a) Before the accumulation of 25,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later: Perform a detailed visual inspection to detect cracking of fuselage frame 07 in the left and right upper frame section assemblies of the lateral cockpit windows, in accordance with Airbus Service Bulletin A300-53-6120 (for Model A300-600 series airplanes) or A310-53-2109 (for Model A310 series airplanes), both dated May 5, 2000; as applicable. Note 2: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” (1) If no cracking is found: Repeat the inspection thereafter at least every 7,000 flight cycles. (2) If any cracking is found and the cracking is only in “area A,” as depicted in view B of Figure 4 of the service bulletin: Before further flight, do the actions specified by either paragraph (a)(2)(i) or (a)(2)(ii) of this AD. (i) Do a temporary repair per the applicable service bulletin. Within 3,000 flight cycles thereafter, do a permanent repair per the applicable service bulletin. Within 32,000 flight cycles thereafter, except as required by paragraph (b) of this AD, repeat the inspection specified by paragraph (a) of this AD. (ii) Do a permanent repair per the applicable service bulletin. Within 32,000 flight cycles thereafter, except as required by paragraph (b) of this AD, repeat the inspection specified by paragraph (a) of this AD. (3) If any cracking is in “area B,” or in both “area A” and “area B” as depicted in view B of Figure 4 of the service bulletin: Before further flight, do a permanent repair per the applicable service bulletin. Within 32,000 flight cycles thereafter, except as required by paragraph (b) of this AD, repeat the inspection specified by paragraph (a) of this AD. (b) If the service bulletin specifies to contact Airbus for further instructions for a repair or inspection: Prior to further flight, perform a repair or inspection per a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). Alternative Methods of Compliance (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. 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. Special Flight Permits (d) 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 (e) Except as required by paragraph (b) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-53-6120, dated May 5, 2000; or Airbus Service Bulletin A310-53-2109, dated May 5, 2000; as applicable. 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 2000-263-314(B), dated June 28, 2000. Effective Date (f) This amendment becomes effective on May 29, 2001. Issued in Renton, Washington, on April 12, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-9665 Filed 4-20-01; 8:45 am] BILLING CODE 4910-13-U