Airworthiness Directive · Amendment 39-19113 · Fuselage
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers on which Airbus modification 05438 has been embodied in production, except those on which Airbus modification 12046 has been embodied in production.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
(5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.
We are superseding Airworthiness Directive (AD) 2016-20-11, which applied to certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Airbus Model A310 series airplanes. AD 2016-20-11 required repetitive inspections of the external area of the aft cargo door sill beam for cracking, repetitive inspections for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, and repair if necessary. This new AD retains the inspections for cracking, and repair if necessary; and requires reinforcement of the aft cargo door sill beam area. This AD was prompted by the development of a reinforcement modification of the aft cargo door sill beam area, which constitutes terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2016-20-11, with no changes. Within the compliance time identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable: Do an ultrasonic inspection or detailed inspection of the aft cargo door sill beam external area for cracking, in accordance with Airbus Alert Operators Transmission (AOT) A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14, Revision 01, dated April 29, 2014. Repeat the inspection thereafter at intervals not to exceed 275 flight cycles. As of January 3, 2017 (the effective date of AD 2016-20-11), use only Airbus AOT A53W005-14, Revision 01, dated April 29, 2014, to comply with the requirements of this paragraph.
(1) For airplanes that have accumulated 30,000 flight cycles or more since the airplane's first flight as of July 2, 2014 (the effective date of AD 2014-12-06, Amendment 39-17867, (79 FR 34403, June 17, 2014) (“AD 2014-12-06”)): Within 50 flight cycles after July 2, 2014.
(2) For airplanes that have accumulated 18,000 flight cycles or more, but fewer than 30,000 flight cycles since the airplane's first flight as of July 2, 2014 (the effective date of AD 2014-12-06): Within 275 flight cycles after July 2, 2014.
(3) For airplanes that have accumulated fewer than 18,000 flight cycles since the airplane's first flight as of July 2, 2014 (the effective date of AD 2014-12-06): Before exceeding 18,275 flight cycles since the airplane's first flight.
This paragraph restates the provisions of paragraph (h) of AD 2016-20-11, with no changes. Accomplishment of a high frequency eddy current (HFEC) inspection for cracking, in accordance with Airbus AOT A53W005-14, dated April 22, 2014; or AOT A53W005-14, Revision 01, dated April 29, 2014; terminates the repetitive inspections required by paragraph (g) of this AD for that airplane. If any cracking is found during the HFEC inspection, 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's EASA Design Organization Approval (DOA).
This paragraph restates the requirements of paragraph (i) of AD 2016-20-11, with no changes. Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to “Airbus Service Bulletin Reporting Online Application” on Airbus World (https://w3.airbus.com/), at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the inspection results, including no findings.
(1) If the inspection was done on or after January 3, 2017 (the effective date of AD 2016-20-11): Submit the report within 30 days after the inspection.
(2) If the inspection was done before January 3, 2017 (the effective date of AD 2016-20-11): Submit the report within 30 days after January 3, 2017.
This paragraph restates the definitions specified in paragraph (j) of AD 2016-20-11, with no changes. Paragraphs (k)(1), (k)(2), and (k)(3) of this AD refer to airplane groups, as identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD.
(1) Airplanes on which an HFEC inspection was accomplished as specified in Airbus AOT A53W005-14.
(2) Airplanes on which no HFEC inspection was accomplished as specified in Airbus AOT A53W005-14, that have accumulated more than 18,000 total flight cycles as of January 3, 2017 (the effective date of AD 2016-20-11).
(3) Airplanes on which no HFEC inspection was accomplished as specified in Airbus AOT A53W005-14, that have accumulated 18,000 total flight cycles or fewer as of January 3, 2017 (the effective date of AD 2016-20-11).
This paragraph restates the requirements of paragraph (k) of AD 2016-20-11, with no changes. At the applicable time specified in paragraph (k)(1), (k)(2), or (k)(3) of this AD: Do an HFEC inspection for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, in accordance with Airbus Service Bulletin A300-53-6179, dated December 12, 2014; or Airbus Service Bulletin A310-53-2139, dated December 12, 2014; as applicable. Repeat the HFEC inspection thereafter at intervals not to exceed 4,600 flight cycles.
(1) For airplanes identified in paragraph (j)(1) of this AD: Inspect within 4,600 flight cycles after the most recent HFEC inspection specified in Airbus AOT A53W005-14.
(2) For airplanes identified in paragraph (j)(2) of this AD: Inspect within 2,000 flight cycles after January 3, 2017 (the effective date of AD 2016-20-11).
(3) For airplanes identified in paragraph (j)(3) of this AD: Inspect before exceeding 13,000 total flight cycles since the airplane's first flight, or within 2,000 flight cycles after January 3, 2017 (the effective date of AD 2016-20-11), whichever occurs later.
This paragraph restates the requirements of paragraph (l) of AD 2016-20-11, with no changes. If any crack is found during any inspection required by paragraph (g) or (k) of this AD: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA.
This paragraph restates the terminating action of paragraph (m)(1) of AD 2016-20-11, with no changes. For any airplane identified in paragraphs (j)(2) and (j)(3) of this AD, accomplishment of the initial inspection required by paragraph (k) of this AD terminates the repetitive inspections required by paragraph (g) of this AD.
At the latest of the applicable times specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD: Reinforce the aft cargo door sill beam area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6181, Revision 01, dated July 2, 2015; or Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2, 2015; as applicable.
(1) Before exceeding 19,600 flight cycles since first flight of the airplane.
(2) Within 2,300 flight cycles after the last HFEC or detailed inspection required by this AD that was accomplished before the effective date of this AD.
(3) Within 12 months after the effective date of this AD.
Modification of an airplane as required by paragraph (n) of this AD constitutes terminating action for the repetitive inspections required by paragraphs (g) and (k) of this AD for the modified airplane 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.
