Airworthiness Directive · Amendment 39-18372 · Stabilizers
Airbus Airplanes
This AD applies to all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and Model A300 F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; certificated in any category.
We are adopting a new airworthiness directive (AD) for all Airbus Model A310 and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a report of skin disbonding and damage found on the composite side panel of the rudder, located between the rudder core and skin of a previously repaired area. This AD requires an inspection for disbonding or damage of certain rudders, and related investigative actions and corrective actions if necessary. We are issuing this AD to detect and correct disbonding and damage of the rudder, which could result in reduced structural integrity of the rudder and consequent reduced controllability of the airplane.
Within 4 months after the effective date of this AD: Check the applicable rudder maintenance records to determine if any composite side shell panel repair has been done since first installation of the rudder, and do the applicable actions specified in paragraph (g)(1) or (g)(2) of this AD at the time specified in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable, except as provided by paragraph (j)(3) of this AD.
(1) If a repair is identified based on the maintenance records: Perform a rudder thermography inspection of the repaired area only for disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable.
(2) If the rudder maintenance records are unavailable or incomplete: Perform a rudder thermography inspection of the complete side shell panels to identify and mark the repair locations for disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable.
If any disbonding or damage is found during any inspection required by paragraph (g)(1) or (g)(2) of this AD: Do the actions required by paragraphs (h)(1) and (h)(2) of this AD, as applicable.
(1) At the time specified in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable, except as required by paragraph (j)(1) of this AD; do the applicable related investigative actions identified in Tables 3, 4A, 4B, 4C, 4D, and 5 of paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable, to determine the type and extent of the disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable. Repeat the applicable inspection at the time specified in paragraph 1.E., “Compliance” of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable.
(2) Before further flight: Repair any disbonding or damage found during any inspection required by paragraph (h)(1) of this AD, or replace any affected rudder, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable, except as required by paragraph (j)(4) of this AD.
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 A310-55-2051; or Figure A-GBBAA (Sheet 01, 02, or 03) or Figure A-GBCAA (Sheet 02 or 04) of Airbus Service Bulletin A300-55-6050; as applicable.
(1) Where Airbus Service Bulletins A300-55-6050; and A310-55-2051; both Revision 01, both dated August 20, 2014; specify a compliance time “from original service bulletin issue date,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) Where Airbus Service Bulletins A300-55-6050; and A310-55-2051 both Revision 01, both dated August 20, 2014; specify to contact Airbus for appropriate action: 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).
(3) Airplanes on which a rudder is installed having a serial number that is not in the range HF-1005 through HF-1323, inclusive; HF-1325, HF-1327, HF-1329, HF-1331, HF-1332, HF-1340, TS-1324, TS-1326, TS-1328, TS-1330, TS-1333 through TS-1339, inclusive; TS-1341 through TS-1420, inclusive; or TS-2001 through TS-2197, inclusive; are not affected by the requirements of paragraphs (g) and (h) of this AD, provided that no repairs have been done in accordance with the applicable SRM specified in paragraph (i) of this AD on the composite side shell panel of that rudder since installation.
(4) The compliance time for the initial detailed inspection of the restored area for loose or lost tape identified in Tables 3 and 4 of paragraph 1.E., “Compliance,” of Airbus Service Bulletins A300-55-6050 and A310-55-2051, both Revision 01, both dated August 20, 2014; specifies “within 500 FH or 4 months after closing holes.” This AD requires this action within 500 flight hours or 4 months, whichever occurs later, after the holes are closed.
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.
