Airworthiness Directive · Amendment 39-14413 · Airbus Model A330-300, A340-200, and A340-300 Series Airplanes
Airbus Model A330-300, A340-200, and A340-300 Series Airplanes
This AD applies to the airplanes, certificated in any category, listed in Table 1 of this AD.
| 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. |
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A330-300, A340-200, and 340-300 series airplanes. The existing AD requires repetitive inspections to detect cracking of the fuselage skin in the area of the VHF2 antenna, and repair if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. This new AD requires accomplishment of the previously optional terminating action, and revises the applicability by removing certain airplanes. This AD is 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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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 flight hours 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.”
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.
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.
(i) If any crack is 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 is longer 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 Générale 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).
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 accordance with an applicable source listed in Table 2 of this AD is acceptable for compliance with the corresponding requirements of paragraph (k) of this AD.
| 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. |
