Airworthiness Directive · Amendment 39-14811 · Airbus Model A330 Airplanes and Model A340-200 and -300 Series Airplanes
Airbus Model A330 Airplanes and Model A340-200 and -300 Series Airplanes
This AD applies to Airbus Model A330 airplanes and Model A340-200 and -300 series airplanes, certificated in any category; on which Airbus Modification 41114 or 44599 was done during production; except those airplanes on which Airbus Modification 53883 was done during production.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330 airplanes and Model A340-200 and -300 series airplanes. This AD requires repetitive detailed inspections for cracking in the aft web of support rib 6 between certain bottom skin stringers on both wings; high frequency eddy current inspections for cracking of the attachment holes of the fuel pipes, and repair if necessary. This AD also provides for an optional modification, which extends a certain inspection threshold, and mandates, for certain airplanes, a new modification of support rib 6 on both wings, which ends the repetitive inspection requirement. This AD results from a report of significant cracking found in the aft web of support rib 6 on both wings. We are issuing this AD to prevent cracking in the aft web of support rib 6, which could result in overloading of adjacent ribs and the surrounding wing structure and consequent reduced structural integrity of the wing.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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.”
For Model A330 series airplanes on which Airbus Modification 53882 was not done during production: At the applicable time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, perform a detailed inspection for cracking in the aft web of support rib 6 between bottom skin stringers 18 and 20 on both wings, and high frequency eddy current inspections for cracking of the attachment holes of the fuel pipe and fuel pipe mounting, by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3085, Revision 02, dated September 29, 2005. If no crack is found during the initial inspections, repeat the inspections thereafter at intervals not to exceed 8,000 flight cycles or 25,000 flight hours, whichever is first, until the terminating action specified in paragraph (n) of this AD is done. If any crack is found during any inspection, repair as specified in paragraph (k) of this AD, or before further flight do the terminating action specified in paragraph (n) of this AD.
(1) For airplanes that have accumulated 7,999 or fewer total flight cycles, and 24,999 or fewer total flight hours, as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total flight cycles or 25,000 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 8,000 or more total flight cycles, but fewer than 10,000 total flight cycles; or 25,000 or more total flight hours, but fewer than 30,000 total flight hours; as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or 30,000 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(3) For airplanes that have accumulated 10,000 or more total flight cycles or 30,000 or more total flight hours as of the effective date of this AD: Do the inspections within 3 months after the effective date of this AD.
(g) For Model A330 series airplanes on which Airbus Modification 53882 was done during production or on which Airbus Service Bulletin A330-57-3087, dated February 15, 2005, or Revision 01, dated September 22, 2005, has been done: Perform the applicable inspections required by paragraph (f) of this AD at the earliest of the initial inspection thresholds specified in Figure 4, Sheet 1, “Inspection Flow Chart” of Airbus Service Bulletin A330-57-3085, Revision 02, dated September 29, 2005; or within 6 months after the effective date of this AD, whichever is later. Repeat the inspections required by paragraph (f) of this AD at the time specified in paragraph (f) of this AD, until the terminating action specified in paragraph (n) of this AD is done.
(h) For Model A340 series airplanes on which Airbus Modification 53882 was not done during production: Perform the inspections required by paragraph (f) of this AD at the applicable time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Perform the inspections by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4093, Revision 02, dated September 29, 2005. Repeat the inspections thereafter at intervals not to exceed 8,000 flight cycles or 30,200 flight hours, whichever is first, until the terminating action specified in paragraph (n) of this AD is done.
(1) For airplanes that have accumulated 7,999 or fewer total flight cycles, and 30,199 or fewer total flight hours, as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total flight cycles or 30,200 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 8,000 or more total flight cycles, but fewer than 10,000 total flight cycles; or 30,200 or more total flight cycles, but fewer than 43,700 total flight hours, as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or 43,700 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(3) For airplanes that have accumulated 10,000 or more total flight cycles or 43,700 or more total flight hours as of the effective date of this AD: Do the inspections within 3 months after the effective date of this AD.
(i) For Model A340 series airplanes on which Airbus Modification 53882 was done during production or on which Airbus Service Bulletin A340-57-4095, dated February 15, 2005, or Revision 01, dated September 22, 2005, has been done: Perform the applicable inspections required by paragraph (f) of this AD at the earliest of the initial inspection thresholds specified in Figure 4, Sheet 1, “Inspection Flow Chart” of Airbus Service Bulletin A340-57-4093, Revision 02, dated September 29, 2005; or within 6 months after the effective date of this AD, whichever is later. Repeat the inspections required by paragraph (f) of this AD at the time specified in paragraph (h) of this AD, until the terminating action specified in paragraph (n) of this AD is done.
Inspections accomplished before the effective date of this AD according to Airbus All Operator Telex A330-57A3085 or A340-57A4093, each dated December 15, 2004; or Airbus Service Bulletin A330-57-3085 or A340-57-4093, each Revision 01, each dated March 25, 2005; are considered acceptable for compliance with the corresponding inspections specified in this AD.
If any cracking is found during any inspection required by this AD: Before further flight, either repair and get a schedule for subsequent inspections, according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent); or accomplish the terminating action specified in paragraph (n) of this AD.
Accomplishing the modification of the fuel pipe connector and the fastener holes of support rib 6 on both wings by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A330-57-3087 or A340-57-4095, each dated February 15, 2005, or Revision 01, each dated September 22, 2005, as applicable, extends the interval for the next inspection to the applicable post-modification inspection threshold specified in Figure 4, Sheet 1, “Inspection Flow Chart” of Airbus Service Bulletins A330-57-3085 or A340-57-4093, each Revision 02, each dated September 29, 2005, as applicable. After accomplishing that inspection, repeat the applicable inspections required by paragraph (f) or (h) of this AD at the applicable repetitive inspection interval specified in Figure 4 of the Accomplishment Instructions of the applicable service bulletin, until the terminating action specified in paragraph (n) of this AD is done.
For Model A330 series airplanes with 8,000 or more total flight cycles or 25,000 or more total flight hours, and Model A340 series airplanes with 8,000 or more total flight cycles or 30,200 or more total flight hours that have not been modified in accordance with paragraph (n) of this AD: Before further flight after any hard or overweight landing of the airplane, accomplish the applicable follow-on inspections and any applicable corrective actions according to a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent). Accomplishing the inspections in Chapter 05-51-11, titled “Inspection After Hard/Overweight Landing—Inspection/Check,” dated April 1, 2005, or July 1, 2006, of the Airbus A330 Aircraft Maintenance Manual (AMM); or Chapter 05-51-11, titled “Inspection After Hard/Overweight Landing—Inspection/Check,” dated July 1, 2006, of the Airbus A340 AMM; as applicable; and Airbus A330/A340 Technical Disposition (TD) TD/J1/S3/00608/2005, Issue C, dated April 26, 2005, titled “Inspections following hard landing, both wings,” are approved methods. Operators can obtain the TD from Airbus.
For airplanes on which support rib 6 on both wings has not been repaired in accordance with paragraph (k) of this AD: Within 60 months after the effective date of this AD, modify the fuel pipe connector and the fastener holes of support rib 6 on both wings by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A330-57-3088 or A340-57-4096, each including Appendix 01, each dated September 21, 2005, as applicable. Accomplishing the modification in this paragraph ends the repetitive inspections required by this AD. Repair of support rib 6 on both wings before the effective date of this AD using Airbus A330/A340 Repair Instruction R572-57023, Issue D, dated May 11, 2005; or R572-57026, Issue C, dated December 2005; as applicable, ends the repetitive inspections required by this AD.
