Airworthiness Directive · Amendment 39-14293 · Airbus Model A330-301, -321, -322, -341, and -342 Airplanes; and Model A340-200 and A340-300 Series Airplanes
Airbus Model A330-301, -321, -322, -341, and -342 Airplanes; and Model A340-200 and A340-300 Series Airplanes
Superseded. A later AD replaced this one: AD 2018-03-08. Comply with the one in force.
This AD applies to Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; except airplanes on which Airbus Modification 41300 or 42547 has been accomplished, as applicable.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires repetitive inspections for cracks in the aft face of the rear spar at the area adjacent to the bolt holes and the end of the build slot, and repair if necessary. The AD also provides an optional terminating action for the repetitive inspections. This AD results from a report that, during fatigue tests of the wing, cracks were found in the vertical web of the rear spar between ribs 1 and 2 having initiated at the build slot. We are issuing this AD to detect and correct fatigue cracking in the vertical web of the wing rear spar, which could result in 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.
Unless otherwise specified in this AD, the term “service bulletin,” as used in this AD, means the Accomplishment Instructions of the following service bulletins, as applicable:
(1) For Model A330-301, -321, -322, -341, and -342 airplanes: Airbus Service Bulletin A330-57-3059, Revision 01, dated September 13, 2001; and
(2) For Model A340-211, -212, -213, -311, -312, and -313 airplanes: Airbus Service Bulletin A340-57-4066, Revision 01, dated September 13, 2001.
At the applicable threshold in Table 1 of this AD, do a high frequency eddy current inspection for cracks in the aft face of the rear spar at the area adjacent to the bolt holes and the end of the build slot; and repeat the inspection thereafter at the applicable repetitive interval in Table 1 of this AD, until the repair required by paragraph (k) of this AD is accomplished. Do all inspections in accordance with the applicable service bulletin.
| The later of— | Repetitive interval | The earlier of— |
|---|---|---|
| A330-301, -321, -322, -341, and -342 airplanes | • Before the accumulation of 10,300 total flight cycles or 32,000 total flight hours, whichever occurs earlier; or | • 8,300 flight cycles; and • 25,800 flight hours. |
| • Within 6 months after the effective date of this AD. | ||
| A340-211, -212, -213, -311, -312, and -313 airplanes | • Before the accumulation of 9,800 total flight cycles or total 48,200 flight hours, whichever occurs earlier; or | • 8,200 flight cycles; and • 40,100 flight hours. |
| • Within 6 months after the effective date of this AD. |
If any crack is found during any inspection required by paragraph (g) of this AD, and the crack has not reached the fastener holes “B” or extends to fastener holes “B,” but not beyond, before further flight: Do the temporary repair in accordance with the applicable service bulletin and repeat the inspection thereafter at the applicable interval in paragraph (g) of this AD until the permanent repair required by paragraph (k) of this AD is accomplished.
(i) If any crack is found during any inspection required by paragraph (g) of this AD, and the crack has extended beyond fastener holes “B,”: Before further flight, do the permanent repair in paragraph (k) of this AD.
(j) Where the service bulletin specifies that operators may contact the manufacturer for instructions on how to repair cracks that extend beyond the modification cut-out area: Before further flight, repair according to a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent).
Doing the permanent repair in accordance with the applicable service bulletin in paragraph (k)(1) or (k)(2) of this AD terminates the repetitive inspection requirements of this AD. Where the service bulletins in paragraph (k)(1) and (k)(2) of this AD specify that operators may contact the manufacturer for instructions on how to repair certain conditions: Before further flight, repair according to a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent).
(1) For Model A330-301, -321, -322, -341, and -342 airplanes: Airbus Service Bulletin A330-57-3058, dated August 29, 2001.
(2) For Model A340-211, -212, -213, -311, -312, and -313 airplanes: Airbus Service Bulletin A340-57-4065, dated August 29, 2001.
Actions done before the effective date of this AD in accordance with the service bulletins identified in Table 2 of this AD, are acceptable for compliance with the corresponding action required by this AD.
| Airbus Service Bulletins | Date |
|---|---|
| A330-57-3059 | March 16, 2001. |
| A340-57-4066 | March 16, 2001. |
