Airworthiness Directive · Amendment 39-17556 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A320-214, -232, and -233 airplanes; and Model A321-211, -213, and -231 airplanes; certificated in any category; manufacturer serial numbers 4338, 4371, 4374, 4375, 4377, 4381 through 4384 inclusive, 4386, 4387, 4388, 4390 through 4402 inclusive, 4404 through 4409 inclusive, 4411 through 4417 inclusive, 4419, 4420, 4421, 4423, 4424, 4426, 4429 through 4436 inclusive, 4438 through 4443 inclusive, 4445 through 4450 inclusive, 4453, 4454, 4456 through 4469 inclusive, 4471, 4472, 4474 through 4481 inclusive, 4483 through 4498 inclusive, 4500, 4504, 4505, 4506, and 4509.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-214, -232 and -233 airplanes; and Model A321-211, - 213, and -231 airplanes. This AD was prompted by a report of a missing fastener between certain stringers of the fuselage frame that connects the frame to a tee. This AD requires an inspection for a missing fastener, and a rototest inspection and a modification or repair of the fuselage frame at the affected area if necessary. We are issuing this AD to detect and correct cracking in the fuselage that could result in reduced 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 24,000 total flight cycles since first flight of the airplane, or within 30 days after the effective date of this AD, whichever occurs later, do the actions specified in paragraph (g)(1) or (g)(2) of this AD.
(1) Do a general visual inspection for a missing fastener between the two fasteners at fuselage frame (FR) 24 between stringer 25 and stringer 26 right-hand side, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-53-1247, Revision 01, dated October 15, 2012.
(i) If the fastener is not missing, no further action is required by paragraph (g) of this AD.
(ii) If the fastener is missing, before further flight, do the actions required by paragraph (g)(2) of this AD.
(2) Do a rototest inspection for cracking of the two adjacent fastener holes at
fuselage FR 24 between stringer 25 and stringer 26 right-hand side, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1247, dated July 15, 2011; or Airbus Mandatory Service Bulletin A320-53-1247, Revision 01, dated October 15, 2012.
(1) If, during the rototest inspection specified by paragraph (g)(2) of this AD, any crack is found, 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 its delegated agent).
(2) If, during the rototest inspection specified by paragraph (g)(2) of this AD, no crack is found, before the accumulation of 24,000 total flight cycles since first flight of the airplane, or within 30 days after the effective date of this AD, whichever occurs later: Modify fuselage FR 24 between stringer 25 and stringer 26 right-hand side, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1247, dated July 15, 2011; or Airbus Mandatory Service Bulletin A320-53-1247, Revision 01, dated October 15, 2012.
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.
