Airworthiness Directive · Amendment 39-17918 · Fuselage
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, manufacturer serial numbers (MSN) 5230 through 5300 inclusive, except MSN 5255 and 5295.
(1) Model A319-111, -112, -115, -132, and -133 airplanes.
(2) Model A320-214, -232, and -233 airplanes.
(3) Model A321-211, -231, and -232 airplanes.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -231, and -232 airplanes. This AD requires a detailed inspection for missing fasteners on the frame between certain stringers; for certain airplanes, a rototest inspection of the fastener holes for cracking; and corrective actions if necessary. This AD was prompted by a report that when the cabin lining was removed during a cabin conversion it was discovered that fasteners were missing on the frame. We are issuing this AD to detect and correct missing fasteners which, if not corrected, could affect the structural integrity of the airframe and could result in rapid decompression.
Within 60 flight cycles after the effective date of this AD: Do a detailed inspection to determine if any fasteners are missing on the structure at frame (FR) 24 between stringer (STR) 17 and STR 18 on the right side only, in accordance with the instructions in Airbus Alert Operators Transmission A53N006-14, dated May 13, 2014.
If, during the detailed inspection required by paragraph (g) of this AD, any fastener is found missing: Before the accumulation of 3,300 flight cycles since the airplane's first flight, or within 60 flight cycles after the effective date of this AD, whichever occurs later, do a rototest inspection of the fastener holes for cracking and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1285, dated January 29, 2014, except as required by paragraph (i) of this AD. Do all applicable corrective actions before further flight.
If any crack is found 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 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.
At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD, report both positive and negative results of the inspections required by paragraphs (g) and (h) of this AD, as applicable, to Airbus, Customer Services Engineering, Emeric Mevel, Structure Engineer, Structure Engineering Support—SEES1, Customer Services; telephone +33(0)5 67-19 02 41; fax +33(0) 5 61 93 36 14; email emeric.mevel@airbus.com. The report must include the information specified in Figure A-FRAAA of Airbus Service Bulletin A320-53-1285, dated January 29, 2014.
(1) If the inspection was done on or after the effective date of this AD: Within 30 days after that inspection.
(2) If the inspection was done before the effective date of this AD: Within 30 days after the effective date of this AD.
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.
