Airworthiness Directive · Amendment 39-18315 · Stabilizers
Airbus Airplanes
This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report of skin disbonding on a composite side shell panel of a rudder. This AD requires an inspection to determine if any rudder composite side shell panel has been repaired, a thermography inspection of each rudder that has received this repair, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct skin disbonding on the rudder, which could affect the structural integrity of the rudder, possibly resulting in reduced control of the airplane.
Within 24 months after the effective date of this AD: Inspect the airplane maintenance records to determine if the rudder composite side shell panel has been repaired since first installation of the rudder on an airplane.
If the finding of the inspection required by paragraph (g) of this AD reveals that a rudder repair has been done as described in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014: Within 24 months after the effective date of this AD, do a pulse thermography inspection on the rudder, limited to the repaired area(s), to determine type, location, and size of the repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014.
For each rudder for which maintenance records are not available or are incomplete: Do the actions required by paragraphs (i)(1) and (i)(2) of this AD.
(1) Not later than 3 months before accomplishment of the pulse thermography inspection required by paragraph (i)(2) of this AD, send the serial number of each rudder to Airbus.
(2) Within 24 months after the effective date of this AD, do a pulse thermography inspection on complete rudder side shells to identify and mark the repair location, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014.
After accomplishing the inspections required by paragraphs (h) and (i) of this AD, as applicable: Depending on findings, do the applicable actions specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, except as required by paragraph (l)(2) of this AD. Findings are specified in Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014.
(1) Do all applicable related investigative actions and corrective actions at the applicable times specified in tables 3, 4A, 4B, 4C, 4D, and 5 in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, except as required by paragraph (l)(1) of this AD.
(2) Do all applicable repetitive inspections of the restored and repaired areas at the applicable intervals specified in tables 3, 4A, 4B, 4C, 4D, and 5 in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014.
Airplanes fitted with a rudder having a serial number which is not in the range TS-1001 to TS-1639 inclusive, or TS-2001 to TS-5890 inclusive; or is not TS-5927; are not affected by the requirements of paragraphs (h), (i), and (j) of this AD, provided it is determined that no repairs have been done as described in the structural repair manual (SRM) procedures identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, on the composite side shell panel of that rudder since first installation on an airplane.
(1) Where Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, specifies a compliance time “after the original Service Bulletin issue date,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) If any damage or fluid ingress is found during any inspection required by this AD and Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014, specifies to contact Airbus: Before further flight, repair 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.
As of the effective date of this AD: Except for rudders that meet the requirements of paragraph (k) of this AD, do not install a rudder unless the rudder is inspected prior to installation as specified in paragraphs (h) and (i) of this AD, and all applicable corrective actions required by paragraph (j) of this AD are done.
As of the effective date of this AD, do not accomplish a composite side shell panel repair on any rudder using an SRM procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A320-55-1041, Revision 01, dated February 24, 2014.
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.
