2005-25-20: Fuselage skin.

2005-25-20 Airbus: Amendment 39-14413. Docket No. FAA-2005-23251; Directorate Identifier 2002-NM-20-AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 29, 2005. Affected ADs (b) This AD supersedes AD 2000-05-04. Applicability (c) This AD applies to the airplanes, certificated in any category, listed in Table 1 of this AD. Table 1.--Applicability Except those modified in accordance with any applicable service information listed below: Model Airbus Service Bulletin Or Airbus production modification Airbus Model A330 301, 321, 322, 323, 341, 342, and 343 airplanes. A330 53 3097, Revision 02, dated November 21, 2000 (Airbus Modification 46025). A330 53 3112, dated February 15, 2001 (Airbus Modification 46849). 46900. Airbus Model A340 211, 212, and 213 airplanes, and Airbus Model A340 311, 312, and 313 airplanes. A340 53 4108,Revision 02, dated December 6, 2000 (Airbus Modification 46025). A340 53 4124, dated February 15, 2001 (Airbus Modification 46849). 46900. Unsafe Condition (d) This AD was prompted by the need to change the applicability of the existing AD and to mandate the formerly optional terminating action. We are issuing this AD to prevent cracking of the fuselage skin in the area of the VHF2 antenna, which could result in depressurization of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2000-05-04 Detailed Inspection (f) At the latest of the times specified in paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of this AD, as applicable: Perform a detailed inspection (without removal of the VHF2 antenna) of the fuselage skin aft of frame 54, between the airplane centerline and stringer 56R in the area of the VHF2 antenna to detect cracks, in accordance with Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001 (for Model A330 series airplanes); or Airbus Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001 (for Model A340 series airplanes). Thereafter, if no cracks are detected, repeat the detailed inspection every 36 flight hours until accomplishment of the high frequency eddy current (HFEC) inspection required by paragraph (g) of this AD. (1) Prior to the accumulation of 900 total flight hours. (2) Within 1,250 flight hours since accomplishment of the interim repair specified by paragraph C.(4) of the Accomplishment Instructions of the applicable service bulletin, if the interim repair has been accomplished prior to April 12, 2000 (the effective date of AD 2000-05-04). (3) Within 300 flighthours since the most recent HFEC inspection accomplished in accordance with the applicable service bulletin, if the most recent HFEC inspection has been accomplished prior to April 12, 2000. (4) Within 36 flight hours after April 12, 2000. Note 1: For the purposes of this AD, a detailed inspection is: "An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required." High Frequency Eddy Current Inspection (g) Perform an HFEC inspection to detect cracks of the fuselage skin aft of frame 54, between the airplane centerline and stringer 56R in the area of the VHF2 antenna, in accordance with Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; or Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; at the applicable time specified by paragraph (g)(1) or (g)(2) of this AD. Accomplishment of this inspection terminates the requirements of paragraph (f) of this AD. (1) For airplanes on which the interim repair specified by paragraph C.(4) of the Accomplishment Instructions of the applicable service bulletin has not been accomplished before April 12, 2000: Prior to the accumulation of 900 total flight hours on the airplane, or within 500 flight hours after April 12, 2000, whichever occurs later. Thereafter, accomplish the follow-on actions of paragraph (h) or (i) of this AD, as applicable. (2) For airplanes on which the interim repair specified by paragraph C.(4) of the Accomplishment Instructions of the applicable service bulletin has been accomplished before April 12, 2000: Within 1,250 flight hours after accomplishment of the interim repair, or within 500 flight hours after April 12, 2000, whichever occurs later. Repetitive Inspections (h) If no crack is detected during the HFEC inspection required by paragraph (g) of this AD, accomplish the repetitive inspections required by paragraph (h)(1) or (h)(2) of this AD, as applicable, until the terminating action required by paragraph (k) of this AD has been done. (1) For airplanes on which the interim repair specified by paragraph C.(4) of the Accomplishment Instructions of Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; or Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; has not been accomplished before April 12, 2000: Accomplish the actions specified by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.(i) Repeat the HFEC inspection specified by paragraph (g) at intervals not to exceed 500 flight hours. (ii) Within 300 flight hours after each HFEC inspection required by this AD: Perform a detailed inspection (without removal of the VHF2 antenna) of the fuselage skin aft of frame 54, between the airplane centerline and stringer 56R in the area of the VHF2 antenna to detect cracks, in accordance with the applicable service bulletin. Thereafter, if no cracks are detected, repeat the detailed inspection at intervals not to exceed 36 flight hours until accomplishment of the next HFEC inspection required by paragraph (h)(1)(i) of this AD. (2) For airplanes on which the interim repair specified by paragraph C.(4) of the Accomplishment Instructions of the applicable service bulletin has been accomplished before April 12, 2000: Repeat the HFEC inspection specified by paragraph (g) of this AD at intervals not to exceed 1,250 flight hours. Corrective Actions (i) If any crackis detected during any inspection required by paragraph (k), (l), or (m) of this AD, and the interim repair specified by paragraph C.(4) of the Accomplishment Instructions of Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; or Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; has not been accomplished: Prior to further flight, accomplish the actions specified by paragraph (i)(1) or (i)(2) of this AD, as applicable. (1) If only one crack is detected and that crack is 9.45 inches or less, and is within the limits specified by the applicable service bulletin: Install the interim repair specified in paragraph C.(4) of the Accomplishment Instructions of the applicable service bulletin. Thereafter, repeat the HFEC inspection specified by paragraph (g) of this AD at intervals not to exceed 1,250 flight hours, until the terminating action required by paragraph (k) of this AD has been done. Note 2: The interim repair referenced by this AD consists of cutting out the cracked portion of the fuselage skin, and installing a filler plate in the skin cutout, two doublers, and shims, as described in paragraph C.(4) of the Accomplishment Instructions of Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001 (for Model A330 series airplanes); or Airbus Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001 (for Model A340 series airplanes). Note 3: Accomplishment of the interim repair in accordance with paragraph 4.3 of Airbus Industrie All Operator Telex (AOT) 53-10, dated September 24, 1997, is acceptable for compliance with the requirements of paragraph (i)(1) of this AD. (2) If any crack is detected that islonger than 9.45 inches, or is outside the limits specified by the service bulletin, or if more than one crack is detected: Repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction G n rale de l'Aviation Civile (DGAC) (or its delegated agent). (j) If any crack is detected during any inspection required by paragraph (f), (g), or (h) of this AD, and the interim repair specified by paragraph C.(4) of the Accomplishment Instructions of Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; or Airbus Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 2001; has been accomplished: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent). New Requirements of This AD Terminating Action (k) Within 18 months after the effective date of this AD: Do the actions specified in either paragraph (k)(1) or (k)(2). Accomplishment of either action terminates the repetitive inspections required by paragraphs (f), (g), (h) and (i)(1) of this AD. (1) Reinforce the fuselage skin between FR54 and FR55 in the area of the VHF2 antenna, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3097, Revision 02, dated November 21, 2000 (for Model A330 series airplanes); or A340- 53-4108, Revision 02, dated December 6, 2000 (for Model A340 series airplanes); as applicable. (2) Relocate the VHF2 antenna between stringer 51 and stringer 52, in accordance with Airbus Service Bulletin A330-53-3112 (for Model A330 series airplanes) or A340-53-4124 (for Model A340 series airplanes), both dated February 15, 2001; as applicable. (l) Work done before the effective date of this AD in accordancewith an applicable source listed in Table 2 of this AD is acceptable for compliance with the corresponding requirements of paragraph (k) of this AD. Table 2.--Credit for Prior Modification Model Service information Revision Date A330 300 Airbus Service Bulletin A330 53 3097 Original July 29, 1998. A330 300, A340 Airbus production Modification 46025 (done in production) A340 Airbus Service Bulletin A340 53 4108 Original July 31, 1998. Alternative Methods of Compliance (m)(1) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (n) The subject of this AD is addressed in French airworthiness directives2001-040(B) and 2001-041(B), both dated January 24, 2001. Material Incorporated by Reference (o) Unless otherwise specified in this AD, the actions must be done in accordance with the service information listed in Table 3 of this AD, as applicable. Table 3.--Material Incorporated by Reference Airbus Service Bulletin Revision level Date A330 53 3094 02 May 28, 1998. A330 53 3094 03 February 22, 2001. A330 53 3094 04 July 23, 2001. A330 53 3097 02 November 21, 2000. A330 53 3112 Original February 15, 2001. A340 53 4105 02 May 25, 1998. A340 53 4105 03 February 22, 2001. A340 53 4105 04 July 23, 2001. A340 53 4108 02 December 6, 2000. A340 53 4124 Original February 15, 2001. (1) The incorporation by reference of the service information listed in Table 4 of this AD is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table 4.--Material Newly Incorporated by Reference Airbus Service Bulletin Revision level Date A330 53 3094 03 February 22, 2001. A330 53 3094 04 July 23, 2001. A330 53 3097 02 November 21, 2000. A330 53 3112 Original February 15, 2001. A340 53 4105 03 February 22, 2001. A340 53 4105 04 July 23, 2001. A340 53 4108 02 December 6, 2000. A340 53 4124 Original February 15, 2001. (2) The incorporation by reference of the service information listed in Table 5 of this AD was approved previously by the Director of the Federal Register as of April 12, 2000 (65 FR 12075, March 8, 2000). Table 5.--Material Previously Incorporated by Reference Airbus Service Bulletin Revision level Date A330 53 3094 02 May 28, 1998. A340 53 4105 02 May 25, 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 NationalArchives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.