Airworthiness Directive · Amendment 39-15345 · Wings
Airbus Model A319 and A320 Series Airplanes
This AD applies to Airbus Model A319 and A320 series airplanes, certificated in any category, all certified models, all serial numbers (MSN); except airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. Model A320 series airplanes MSN 2164 through MSN 2688 that have partially received Airbus Modification 33421 in production are affected by the requirements of this AD.
(1) Model A319 series airplanes that have received Airbus Modifications 28238, 28162, and 28342 in production, or Airbus Modification 33421 in production.
(2) Model A320 series airplanes that have received Airbus Modification 33421 fully embodied in production.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions.
(1) For A320-200 aircraft: Before the defined threshold or within the defined grace period after the effective date of this AD, whichever occurs later, as listed in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A320-57-1129, Revision 02, dated July 17, 2007, and following the instructions given in the service bulletin, perform an internal ultrasonic inspection of the lower stiffeners in the center and outer wing box at the level of the rib 1 junction to detect cracks, and if any crack is found, before further flight contact Airbus for repair instructions and repair. Repeat this inspection at the intervals defined in paragraph 1.E., “Compliance,” of the service bulletin. Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1129, Revision 01, dated July 28, 2006, are acceptable for compliance with the corresponding actions of this paragraph.
(2) For all aircraft: Before the defined threshold or within the defined grace period after the effective date of this AD, whichever occurs later, as listed in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A320-57-1130, Revision 02, dated July 17, 2007, and following the instructions given in the service bulletin, perform an external ultrasonic inspection of the lower stiffeners in the center and outer wing box at the level of the rib 1 junction to detect cracks, and if any crack is found, before further flight contact Airbus for repair instructions and repair. Repeat this inspection at the intervals defined in paragraph 1.E., “Compliance,” of the service bulletin. Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1130, dated September 10, 2004; or Revision 01, dated July 28, 2006; are acceptable for compliance with the corresponding actions of this paragraph.
(3) Modification of the aircraft in accordance with the instructions contained in Airbus Service Bulletins A320-57-1131, A320-57-1137, or A320-57-1140, all dated November 21, 2006; terminates the repetitive inspection requirements of this AD.
Note: This AD differs from the MCAI and/or service information as follows: (1) Although the MCAI or service information does not specify a compliance time for corrective action (repair of cracks), paragraphs (f)(1) and (f)(2) of this AD require that the corrective action be done before further flight.
(2) Although the MCAI and/or service information specify a compliance time for accomplishing the inspections after the effective date of the MCAI, this AD requires compliance within the specified compliance time after the effective date of this AD.
