Airworthiness Directive · Amendment 39-14277 · 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
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; on which Airbus Modification 42418 has not been accomplished in production.
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 of the inboard lower flange and radius of the left- and right-hand outboard floor beams at frame (FR) 48, and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports that cracks were found during fatigue tests at the attachment between the canted lower flange of the floor beam and the pressure diaphragm in front of FR48 on both left- and right-hand floor beams; and that an additional crack was found in the flange radius of the floor beam. We are issuing this AD to detect and correct such cracking, which could propagate and result in reduced structural integrity of the fuselage.
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 applicable times in paragraph (f)(1) or (f)(2) of this AD: Do high-frequency eddy current inspection for cracks of the inboard lower flange and radius of the left-hand and right-hand outboard floor beams at FR48. Do all inspections in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 1 of this AD. Doing the action in paragraph (h) of this AD terminates the repetitive inspection requirements of this paragraph.
(1) For Airbus Model A330-301, -321, -322, -341, and -342 airplanes: Do the first inspection before the accumulation of 8,400 flight cycles since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later; and repeat the inspection thereafter at intervals not to exceed 3,860 total flight cycles or 15,050 flight hours, whichever occurs earlier.
(2) For Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes: Do the first inspection before the accumulation of the earlier of 9,200 flight cycles or 70,000 flight hours since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later; and repeat the inspection thereafter at intervals not to exceed 3,070 flight cycles.
| For airbus model— | Airbus service bulletin— |
|---|---|
| A330-301, -321, -322, -341, and -342 airplanes | A330-53-3014, Revision 05, dated June 20, 2003. |
| A340-211, -212, -213, -311, -312, and -313 airplanes | A340-53-4022, Revision 05, dated June 16, 2003. |
If any crack is found during any inspection required by paragraph (f) of this AD: Do the applicable actions in paragraph (g)(1) and (g)(2) of this AD.
(1) For cracks at the radius: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Geáneárale de l'Aviation Civile (DGAC) (or its delegated agent).
(2) For cracks at the flange: Before further flight, measure the total length of the crack and do the applicable action in paragraph (g)(2)(i) and (g)(2)(ii) of this AD.
(i) If the crack is less than 12 mm (0.472 inch) in length: Before further flight, stop-drill the crack and, within 500 flight cycles after stop-drilling the crack, do the action in paragraph (h) of this AD.
(ii) If the crack is greater than or equal to 12 mm (0.472 inch) in length: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM-116; or the Direction Geáneárale de l'Aviation Civile (DGAC) (or its delegated agent).
Installing a stainless steel doubler in accordance with Airbus Service Bulletin A330-53-3013, Revision 03, December 23, 1999; or Airbus Service Bulletin A340-53-4021, Revision 05, dated January 27, 2003; as applicable; terminates the repetitive inspection requirements of paragraph (f) of this AD. If any crack is found during this installation while doing the rotating probe inspection of the fastener holes: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
(i) Although the Accomplishment Instructions of the service bulletins identified in Table 1 of this AD describe procedures for reporting certain information to the manufacturer, this AD would not require those actions.
