Airworthiness Directive · Amendment 39-18247 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2019-18-07. Comply with the one in force.
This AD applies to Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all manufacturer serial numbers.
We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by reports that during a full scale fatigue test, several broken frames in certain areas of the cargo compartment have been found, especially on the cargo floor support fittings and open tack holes on the left-hand side. This AD requires a rototest inspection of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions, and repair if necessary. We are issuing this AD to detect and correct cracking in the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, which could affect the structural integrity of the airplane.
At the applicable compliance times specified in paragraphs (g)(1) through (g)(3) of this AD: Do a rototest inspection for cracking of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage between frame (FR) 50 and FR 63 left-hand (LH) side only for Model A320 series airplanes, and A321 series airplanes; and between FR 53 and FR 63 LH side only for Model A319 series airplanes; in accordance with paragraph 3.C., “Procedures,” of the Accomplishment Instructions of Airbus Service Bulletin A320-53-1257, dated December 21, 2012. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs first.
(1) For airplanes that have equal to or more than 45,000 total flight cycles or 90,000 total flight hours as of the effective date of this AD: Do the rototest inspection within 1,000 flight cycles or 2,000 flight hours after the effective date of this AD, whichever occurs first.
(2) For airplanes that have equal to or more than 36,200 total flight cycles or 72,400 total flight hours, but less than 45,000 total flight cycles or 90,000 total flight hours as of the effective date of this AD: Do the rototest inspection within 2,000 flight cycles or 4,000 flight hours after the effective date of this AD, whichever occurs first, but no later than before the accumulation of 46,000 total flight cycles or 92,000 total flight hours, whichever occurs first.
(3) For airplanes that have less than 36,200 total flight cycles or 72,400 total flight hours as of the effective date of this AD: Do the rototest inspection before exceeding 38,200 total flight cycles or 76,400 total flight hours, whichever occurs first.
If any crack is found during any inspection required by 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.
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.
