Airworthiness Directive · Amendment 39-18134 · Stabilizers
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, except airplanes on which modification 08827 has been embodied in production.
(1) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, certificated in any category, all manufacturer serial numbers.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all manufacturer serial numbers.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4- 605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, - 204, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by a report of inner skin disbonding damage on a rudder. This AD requires repetitive ultrasonic inspections for disbonding of certain rudders; an elasticity of laminate checker inspection; a woodpecker or tap test inspection; venting the core, if necessary; and repairing, if necessary. We are issuing this AD to detect and correct rudder disbonding, which could affect the structural integrity of the rudder.
Within 3 months after the effective date of this AD, identify the rudder assembly part number (P/N) and serial number (S/N), in accordance with Airbus Alert Operators Transmission (AOT) A55W002-12, dated December 13, 2012, including Inspection Flowchart. If the part number or serial number cannot be determined, within 3 months after the effective date of this AD, identify the part number and serial number, in accordance with a method approved by either 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).
(1) Except as provided by paragraph (h)(2) of this AD, if a rudder assembly part number starting with A55471500 is found during the inspection required by paragraph (g) of this AD, before further flight, do an ultrasonic (UT) 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 A55W002-12, dated December 13, 2012, including Inspection Flowchart. If any damage is found, before further flight, do the inspections to confirm disbonding damage, as specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, in accordance with Airbus AOT A55W002-12, dated December 13, 2012.
(i) Do an elasticity of laminate checker inspection to detect external and internal disbonding of the rudder side panel along the Z-profile and in the booster area.
(ii) Do a woodpecker or tap test inspection to detect external disbonding of the rudder side panel along the Z-profile and in the booster area.
(2) For airplanes on which it can be conclusively determined that the most recent inspection specified in Airbus Service Bulletin A310-55-2044 or Airbus Service Bulletin A300-55-6043 was done on the airplane; or the rudder was not removed for any reason since doing the most recent inspection specified in Airbus Service Bulletin A310-55-2044 or Airbus Service Bulletin A300-55-6043: No further action is required by this AD, except as specified in paragraphs (j) and (k) of this AD.
(1) If any disbonding is confirmed during any inspection required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, before further flight, repair as specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, as applicable.
(i) If 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 core, using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Within 100 flight cycles after the UT inspection specified in paragraph (h) of this AD is done, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(ii) If 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.
(2) If liquid ingress is confirmed during any inspection required by paragraphs (h)(1)(i) and (h)(1)(ii) 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 any rudder has been inspected as specified in Airbus Service Bulletin A300-55-6043, Revision 01, dated December 3, 2007; or A310-55-2044, Revision 01, dated December 3, 2007; as applicable; and has been removed and re-installed on any airplane after this inspection, that rudder must be re-inspected as required by paragraph (g) of this AD; and all applicable actions required by paragraphs (h) and (i) of this AD must be done.
As of the effective date of this AD, no person may install, on any airplane, a rudder assembly having a part number starting with A55471500, unless it has been inspected as required by paragraph (h) of this AD, and all applicable actions required by paragraph (i) of this AD have been done.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
