Airworthiness Directive · Amendment 39-19453 · Fuselage
Airbus SAS Airplanes
This AD applies to the following Airbus SAS airplanes, certificated in any category, manufacturer serial numbers (MSNs) 0001 to 1779 inclusive; except airplanes on which Airbus Service Bulletin A330-53-3275 or Airbus Service Bulletin A340-53-4238 has been embodied.
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(4) Model A340-211, -212, and -213 airplanes.
(5) Model A340-311, -312, and -313 airplanes.
We are superseding Airworthiness Directive (AD) 2017-16-07, which applied to certain Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A340-500, and A340-600 series airplanes; and Model A340-313 airplanes. AD 2017-16-07 required inspection of the fuselage bulk cargo door frames at specific locations, and corrective action if necessary. This AD requires new inspections of certain attachment holes for residual surface treatment and cracking, and corrective action if necessary; and provides an optional terminating action for the inspections. This AD also revises the applicability to add certain airplanes and remove others. This AD was prompted by a determination that only airplanes having certain manufacturer serial numbers (MSNs) are affected by tartaric sulfuric anodizing (TSA)/chromic acid anodizing (CAA) surface treatment in the door fitting attachment holes, and that airplanes having certain MSNs were excluded. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to address the unsafe condition on these products.
Before exceeding the thresholds specified in table 1 to paragraph (g) of this AD, or within the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, whichever is later: Do a rototest, high frequency eddy current (HFEC), ultrasonic, or detailed inspection, as applicable, for residual surface treatment and cracking of the upper and lower right-hand fuselage bulk cargo door support fitting attachment holes at FR 67 and FR 69 and the right-hand fuselage bulk cargo door latch fitting attachment holes at FR 69, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3278, dated August 22, 2017; or Airbus Service Bulletin A340-53-4239, dated September 5, 2017; as applicable. Thereafter, depending on the areas and inspection methods as defined in table 2 to paragraph (g) of this AD, repeat the inspection at intervals not exceeding those specified in table 3 to paragraph (g) of this AD.
(1) For airplanes having MSN 0001 through 0399 inclusive: Within 200 flight cycles after the effective date of this AD.
(2) For airplanes having MSN 0400 through 1779 inclusive: Within 800 flight cycles after the effective date of this AD.
If any discrepancy is found during any inspection required by paragraph (g) of this AD, before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
Accomplishment of a repair on an airplane, as required by paragraph (h) of this AD, does not constitute terminating action for the inspections required by paragraph (g) of this AD for that airplane, unless otherwise specified in repair instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
Accomplishment of the modification, including applicable related investigative and corrective actions and removal of TSA or CAA in the final holes of the bulk door frames FR 67 and FR 69, as applicable, specified in, and in accordance with the AI of Airbus Service Bulletin A330-53-3275, dated September 8, 2017; or Airbus Service Bulletin A340-53-4238, dated September 8, 2017; as applicable; constitutes terminating action for the inspections required by paragraph (g) of this AD for that airplane, unless otherwise specified in the repair instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA 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.
Aircraft
