Airworthiness Directive · Amendment 39-18928 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2021-17-03. Comply with the one in force.
This AD applies to the Airbus Model A320-212 airplane having manufacturer serial number (MSN) 1011; Airbus Model A320-214 airplanes having MSNs 1009, 1026 and 1030; the Airbus Model A320-232 airplane having MSN 0977; and Airbus Model A320-233 airplanes having MSNs 1007 and 1013; certificated in any category.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-212, -214, -232, and -233 airplanes. This AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame. This AD requires repetitive low frequency eddy current inspections or repetitive high frequency eddy current inspections of this area, and repair if necessary. The repair terminates the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
Within 750 flight cycles or 4 months, whichever occurs first after the effective date of this AD: Do a low frequency eddy current (LFEC) inspection or a high frequency eddy current (HFEC) inspection for cracking of the pocket radii located between fuselage frames 35 and 40, above stringer 6 on both the left- and right-hand sides, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A53N009-14, Rev 00, dated December 17, 2014. Repeat the inspection, thereafter, at intervals not to exceed the times specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) For the LFEC inspection performed on the outside: Repeat the inspection at intervals not to exceed 1,000 flight cycles.
(2) For the HFEC inspection performed on the inside: Repeat the inspection at intervals not to exceed 2,000 flight cycles.
If, during any inspection required by paragraph (g) of this AD, any crack is found, before further flight, accomplish the repair in accordance with the instructions of Airbus AOT A53N009-14, Rev 00, dated December 17, 2014; except if the crack is beyond the structural repair manual limits as specified in Airbus AOT A53N009-14, Rev 00, dated December 17, 2014, 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).
Repair of an airplane as required by paragraph (h) of this AD terminates the repetitive inspections required by paragraph (g) of this AD for the repaired area only.
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.
