Airworthiness Directive · Amendment 39-18078 · Stabilizers
Airbus Airplanes
This AD applies to Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; except airplanes on which Airbus Modification 41800 has been embodied in production.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by a report of substantial inner skin disbonding damage found on a rudder. This AD requires performing an inspection for damage of certain rudders, and repair if necessary. We are issuing this AD to detect and correct damage of the rudder, which could result in reduced structural integrity of the rudder.
Within 3 months after the effective date of this AD, inspect for the rudder assembly part number and serial number, in accordance with Airbus Alert Operators Transmission (AOT) A55L001-12, dated December 20, 2012. If the part number or serial number cannot be identified, within 3 months after the effective date of this AD, identify the part number and serial number using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
If a rudder assembly having any part number starting with A55471500 or A55471500XXX (where XXX stands for any numerical value) is found during the inspection required by paragraph (g) of this AD, and that rudder assembly has been inspected before the effective date of this AD, as specified in Airbus Service Bulletin A330-55-3038, dated November 7, 2007 (which is not incorporated by reference in this AD); or Airbus Service Bulletin A340-55-4034, dated November 7, 2007 (which is not incorporated by reference in this AD); as applicable; and that rudder assembly has been removed and installed on any airplane after the inspection or that has been inspected off-wing: Within 3 months after the effective date of this AD, do an ultrasonic test inspection for damage (e.g., disbonding and liquid ingress) of the rudder side panel along the Z-profile and in the booster area, in accordance with Airbus AOT A55L001-12, dated December 20, 2012. If any damage is found, before further flight, do the inspections specified in paragraphs (h)(1) and (h)(2) of this AD to confirm disbonding damage, in accordance with Airbus AOT A55L001-12, dated December 20, 2012.
(1) Do an elasticity of laminate checker inspection to detect external and internal disbonding.
(2) Do a woodpecker or tap test inspection to detect external disbonding.
If any disbonding or damage (e.g. liquid ingress) is confirmed during any inspection required by paragraphs (h), (h)(1), and (h)(2) of this AD, repair at the time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable.
(1) If the disbonding is less than or equal to 50 millimeters (mm) in width and less than or equal to 150 mm in length: Before further flight, vent the rudder core using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Within 100 flight cycles after venting the rudder core, do a permanent repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval for the venting and repair methods must include the DOA-authorized signature.
(2) If the disbonding is greater than 50 mm in width, or greater than 150 mm in length: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(3) If any damage other than disbonding (e.g., liquid ingress) is confirmed during any inspection required by paragraph (h) of this AD, before further flight, repair, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
As of the effective date of this AD, you may install, on any airplane, a rudder assembly having part number A55471500XXX (where XXX stands for any numerical value), provided the inspection required by paragraph (h) of this AD and all applicable repair actions required by paragraph (i) of this AD are done before further flight.
