AD 2001-17-29 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes, and Model A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes

Models named: A300 B2, B4 series. Read the applicability below — it usually turns on serial or part numbers too.

The following airplanes, certificated in any category: —Model A300 B2 and B4 series airplanes, except those modified by Airbus Modification 11932 (reference Airbus Service Bulletin A300-57-0235, Revision 01, including Appendix 01, dated February 1, 1999; or earlier version); and —Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; manufacturer serial numbers (MSNs) up to and including MSN 787; except those modified by Airbus Modification 11932 (reference Airbus Service Bulletin A300-57-6088, Revision 01, including Appendix 01, dated February 1, 1999; or earlier version). 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 (b) 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 fatigue cracking of the attachment fittings of the main landing gear (MLG), which could result in reduced structural integrity of the airplane, accomplish the following: Note 2: The inspection required by paragraph (a) of this AD is also included in the inspection requirement of paragraph (a) of AD 2000-05-07, amendment 39-11616. As indicated by the phrase, “unless accomplished previously,” for any airplane on which the initial inspection of AD 2000-05-07 has been accomplished before the effective date of this AD, the inspection specified by paragraph (a) of this AD is not required. Inspection (a) Before the accumulation of 7,500 total flight cycles, or within 100 flight cycles after the effective date of this AD, whichever occurs later: Perform a one-time detailed visual inspection to detect cracks in gear rib 5 (left and right) of the MLG attachment fittings at the lower flange and vertical web, in accordance with Airbus All Operators Telex (AOT) A300-57A0239 (for Model A300 B2 and B4 series airplanes) or A300-600-57A6094 (for Model A300-600 series airplanes), both dated August 2, 2001. (1) If any cracking is detected and it is found at one hole only and does not extend out of the spotface of the hole: Prior to further flight, repair in accordance with the applicable AOT. (2) If any cracking is detected and it is found at more than one hole or extends out of the spotface of any hole: Repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (or its delegated agent). Note 3: The AOTs refer to Airbus Service Bulletins A300-57A0234 (for Model A300 B2 and B4 series airplanes) and A300-57A6087 (for Model A300-600 series airplanes) as additional sources of service information for the inspection and repair of any cracking found during the inspection. Note 4: 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.” Alternative Methods of Compliance (b) 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 5: 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 (c) 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 (d) Except as required by paragraph (a)(2) of this AD: The actions must be done in accordance with Airbus All Operators Telex A300-57A0239, dated August 2, 2001; or Airbus All Operators Telex A300-600-57A6094, dated August 2, 2001; 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 6: The subject of this AD is addressed in French telegraphic airworthiness directive T2001-364(B), dated August 2, 2001. Effective Date (e) This amendment becomes effective on September 13, 2001. Issued in Renton, Washington, on August 20, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-21487 Filed 8-28-01; 8:45 am] BILLING CODE 4910-13-P