Airworthiness Directive · Amendment 39-15086 · Airbus Model A340-211, -212, -311, and -312 Airplanes
Airbus Model A340-211, -212, -311, and -312 Airplanes
This AD applies to Airbus Model A340-211, -212, -311, and -312 airplanes, certificated in any category; serial numbers 0006, 0007 (right-hand side of the airplane only), 0008 (left-hand side only), 0013, 0020, 0024 (left-hand side only), 0027 through 0029 inclusive, 0031, 0033, 0035, 0038 through 0040 inclusive, 0043, 0047, 0049, and 0052.
The FAA is superseding an existing airworthiness directive (AD) that applies to certain Airbus Model A340-211, -212, -311, and - 312 airplanes. The existing AD currently requires an initial rotating probe inspection and initial and repetitive ultrasonic inspections for discrepancies of the first fastener hole of the horizontal flange of the keel beam on previously modified airplanes, installation of new fasteners, and corrective action if necessary. This AD retains the actions required by the existing AD and adds new rotating probe inspections and a terminating action for the repetitive inspections of the existing AD. This AD results from a report that certain inspections, done before accomplishing the modification of the lower keel beam fitting and forward lower shell connection, revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. We are issuing this AD to prevent discrepancies of the fastener holes of the horizontal flange of the keel beam, which could 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.
Within 5,420 flight cycles or 26,200 flight hours after accomplishing Airbus Modification 43577, whichever is first: Perform an initial rotating probe inspection for discrepancies of the first fastener hole of the horizontal flange of the keel beam by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4087, dated November 21, 2003; or Revision 01, dated February 15, 2005. If no cracking is found, before further flight, inspect for correct fastener diameter tolerance; if the fastener diameter is out of tolerance, before further flight, ream to oversize the fastener holes and install oversize fasteners in accordance with the Accomplishment Instructions of the service bulletin. Accomplishing the modifications specified in paragraph (i) of this AD ends the requirement for these inspections.
(g) If no cracking is found during any inspection required by paragraph (f) of this AD: Within 1,480 flight cycles or 7,400 flight hours, whichever is first, after accomplishing the inspection, perform an initial ultrasonic inspection for discrepancies of the first fastener hole of the horizontal flange of the keel beam by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4087, dated November 21, 2003; or Revision 01, dated February 15, 2005. If no cracking is found, repeat the ultrasonic inspection thereafter at intervals not to exceed 1,480 flight cycles or 7,400 flight hours, whichever is first; until the modifications required by paragraph (i) of this AD are accomplished.
If any cracking is found during any inspection required by this AD: Before further flight, repair per a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the DGAC (or its delegated agent); or the EASA (or its delegated agent). Within 1,480 flight cycles or 7,400 flight hours, whichever is first, after repair of any cracking, perform an ultrasonic inspection as required by paragraph (g) of this AD. Repeat the ultrasonic inspection thereafter at intervals not to exceed 1,480 flight cycles or 7,400 flight hours, whichever is first; until the actions required by paragraph (i) of this AD are accomplished.
(i) Within 118 months after the effective date of this AD: Disconnect the keel beam from the center wing box panel at fastener hole 5, do applicable rotating probe inspections, and do cold work and install interference fit fasteners in two adjacent fastener holes of the center wing box panel; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4099, dated March 27, 2006, except as required by paragraph (j) of this AD. Accomplishing these actions terminates the inspection requirements of paragraphs (f), (g), and (h) of this AD.
If any crack is found during any action required by paragraph (i) of this AD and Service Bulletin A340-57-4099 specifies to contact Airbus: Before further flight, repair per a method approved by the Manager, International Branch, ANM-116; the DGAC (or its delegated agent); or the EASA (or its delegated agent).
Although Airbus Service Bulletin A340-57-4087, dated November 21, 2003; and Revision 01, dated February 15, 2005, specify submitting an inspection report to the manufacturer, this AD does not include that requirement.
