Airworthiness Directive · Amendment 39-15850 · Wings
Airbus Model A321-131 Airplanes
This AD applies to Airbus Model A321-131 airplanes, certificated in any category, manufacturer serial numbers (MSNs) 364 and 385.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A321-131 airplanes. This AD requires repetitive ultrasonic inspections to detect cracks in the wing inner rear spars at the attachment holes of the Main Landing Gear (MLG) forward pintle fitting, the actuator cylinder anchorage fitting, and rib 5 fitting; and repair of the sealant or repair of any crack. This AD results from a finding that certain A321-131 airplanes may not reach the design life goal due to differences in thickness of the inner rear spars and that fatigue cracks may develop on inner rear spars starting from the fastener holes for the attachment of gear rib 5, the forward pintle fitting, and the actuating cylinder anchorage on these airplanes. We are issuing this AD to detect and correct such fatigue cracks, which 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.
At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD, do an ultrasonic inspection to detect cracks of the left-hand and right-hand wing inner rear spars at the attachment holes of the main landing gear (MLG) forward pintle fitting, the actuator cylinder anchorage fitting, and gear rib 5 fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1126, dated August 8, 2003. Repeat the inspection thereafter at intervals not to exceed 3,600 flight cycles or 5,600 flight hours, whichever occurs first.
(1) Before the accumulation of 24,000 total flight cycles or 39,400 total flight hours from first flight, whichever occurs first.
(2) Within 6 months after the effective date of this AD.
If no crack is detected during any inspection required by paragraph (g) of this AD, before further flight, repair the sealant in the inspected areas in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1126, dated August 8, 2003.
(i) If any crack is detected during any inspection required by paragraph (g) of this AD, before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
