Airworthiness Directive · Amendment 39-17491 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A319-112, -113, and -132 airplanes; Model A320-211, -212, -214, -231, and -232 airplanes; and Model A321-111 and -131 airplanes; certificated in any category; manufacturer serial numbers 0259, 0260, 0264, 0266 through 0270 inclusive, 0275, 0276, 0278, 0287, 0296, 0300, 0303, 0312, 0320, 0321, 0323, 0325, 0328, 0332, 0334, 0335, 0337, 0346, 0352, 0353, 0356, 0365, 0369, 0375, 0377, 0382, 0383, 0396, 0398, 0401, 0412, 0413, 0416, 0419, 0421, 0431, 0432, 0438, 0440, 0441, 0445, 0453, 0458, 0459, 0466, 0468, 0473, 0474, 0482, 0484, 0491, 0493, 0497, 0498, 0501, 0502, 0505, 0507, 0509, 0518, 0520, 0521, 0529, 0531, 0534, 0537, 0538, 0544, 0549, 0554, 0555, 0560, 0563, 0577, 0578, 0585, 0598, 0600, 0608, 0612, 0618, 0621, 0625, 0637, 0660, 0685, 0976, 1010, 1092, 1096, 1103, 1139, 1143, 1158, 1251, 1356, and 1511.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-112, -113, and -132 airplanes; Model A320-211, -212, -214, -231, and -232 airplanes; and Model A321-111 and -131 airplanes. This AD was prompted by a report of two fatigue cracks on the left-hand and right-hand sides of the continuity fittings at the front windshield lower framing on a Model A319 series airplane. This AD requires a high frequency eddy current (HFEC) inspection for any cracking on the left- hand and right-hand sides of the windshield central lower node continuity fittings, and repair if necessary. We are issuing this AD to detect and correct cracking of the windshield central lower node continuity fittings, which could reduce the structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Before the accumulation of 34,000 total flight cycles since the airplane's first flight, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current (HFEC) inspection for any cracking on the left-hand and right-hand sides of the windshield central lower node continuity fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1245, Revision 01, including Appendix 1, dated May 17, 2011. If any cracking is found, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent).
Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to Airbus, Customer Service Directorate, Attn: SDC32 Technical Data and Documentation Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 28 06; email sb.reporting@airbus.com; at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report 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.
