AD 99-02-08 Airworthiness Directives; Airbus Model A330-301, -321, -322, - 341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes

Models named: A330-301, -321, -322, -341, -342 series, A340-211, -212, -213, -311, -312. Read the applicability below — it usually turns on serial or part numbers too.

Model A330-301, -321, -322, -341, and -342 series airplanes, except those on which Airbus Modification 41849 has been installed, or Airbus Modification 43337 (reference Airbus Service Bulletin A330-53-3036, Revision 01, dated December 22, 1997) has been accomplished; and Model A340-211, -212, -213, -311, -312, and - 313 series airplanes, except those on which Airbus Modification 41849 has been installed, or Airbus Modification 43338 (reference Airbus Service Bulletin A340-53-4050, dated February 19, 1997) has been accomplished; certificated in any category. 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 (d) 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 the inner flange of the rear fuselage frame FR73A, which could result in reduced structural integrity of the fuselage, accomplish the following: (a) Perform a high-frequency eddy current (HFEC) inspection to detect cracking of the inner flange (left and right sides) of the rear fuselage frame FR73A, between beams 5 and 6, in accordance with Airbus Service Bulletin A330-53-3037, Revision 01 (for Model A330 series airplanes), or A340-53-4051, Revision 01 (for Model A340 series airplanes), both dated January 30, 1998; at the applicable times specified in paragraph (a)(1) or (a)(2) of this AD. (1) For Model A330 series airplanes: Inspect prior to the accumulation of 10,000 total flight cycles, or within 90 days after the effective date of this AD, whichever occurs later. Thereafter, repeat the HFEC inspection at intervals not to exceed 1,600 flight cycles. (2) For Model A340 series airplanes: Inspect prior to the accumulation of 8,750 total flight cycles, or within 90 days after the effective date of this AD, whichever occurs later. Thereafter, repeat the HFEC inspection at intervals not to exceed 1,200 flight cycles. (b) If any crack is detected during any HFEC inspection required by paragraph (a) of this AD, prior to further flight, accomplish either paragraph (b)(1) or (b)(2) of this AD, in accordance with Airbus Service Bulletin A330-53-3037, Revision 01 (for Model A330 series airplanes), or A340-53-4051, Revision 01 (for Model A340 series airplanes), both dated January 30, 1998. (1) If any crack is less than or equal to 5.0 millimeters (0.20 inch) in length: (i) Prior to further flight, rework the affected area in accordance with the applicable service bulletin; and (ii) Within 2,000 flight cycles after accomplishing the rework of the affected area: Replace the affected area of the rear fuselage frame FR73A with a new, improved section of FR73A in accordance with the applicable service bulletin. This replacement constitutes terminating action for the repetitive HFEC inspections required by paragraph (a) of this AD for the affected area only. (2) If any crack is greater than 5.0 millimeters (0.20 inch) in length: (i) Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent); or (ii) Prior to further flight, replace the affected area of the rear fuselage frame FR73A with a new, improved section of FR73A in accordance with the applicable service bulletin. This replacement constitutes terminating action for the repetitive HFEC inspections required by paragraph (a) of this AD for the affected area only. (c) Accomplishment of the modification of the inner flange (left and right sides), of the rear fuselage frame FR73A, between beams 5 and 6, in accordance with Airbus Service Bulletins A330-53-3036, Revision 01, dated December 22, 1997 (for Model A330 series airplanes), or A340-53-4050, dated February 19, 1997 (for Model A340 series airplanes), constitutes terminating action for the repetitive HFEC inspections required by paragraph (a) of this AD. (d) 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (e) Special flight permits may be issued in accordance with sections 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. (f) Except as provided by paragraph (b)(2)(i) of this AD, the actions shall be done in accordance with Airbus Service Bulletin [[Page 2816]] A330-53-3037, Revision 01, dated January 30, 1998; Airbus Service Bulletin A330-53-3036, Revision 01, dated December 22, 1997; Airbus Service Bulletin A340-53-4051, Revision 01, dated January 30, 1998; or Airbus Service Bulletin A340-53-4050, dated February 19, 1997; 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 3: The subject of this AD is addressed in French airworthiness directives 97-270-055(B) and 97-271-071(B), both dated September 24, 1997. (g) This amendment becomes effective on February 3, 1999. Issued in Renton, Washington, on January 8, 1999. John J. Hickey, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-913 Filed 1-15-99; 8:45 am] BILLING CODE 4910-13-P