Airworthiness Directive · Amendment 39-19714 · Doors
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2024-01-08. Comply with the one in force.
This AD applies to Airbus SAS Model A300 F4-605R and F4-622R airplanes, certificated in any category, on which Airbus modification 12046 has been embodied in production. Modification 12046 has been embodied in production on manufacturer serial numbers (MSNs) 0805 and above, except MSNs 0836, 0837, and 0838.
The FAA is superseding Airworthiness Directive (AD) 2018-20- 06, which applied to certain Airbus SAS Model A300 F4-600R series airplanes. AD 2018-20-06 required repetitive high frequency eddy current (HFEC) inspections of the aft lower deck cargo door (LDCD) frame forks; a one-time check of the LDCD clearances; a one-time detailed visual inspection of hooks, eccentric bushes, and x-stops; and corrective actions if necessary. This AD retains the actions of AD 2018-20-06 and requires new compliance times, depending on frame fork configuration. This AD was prompted by a report of two adjacent frame forks that were found cracked on the aft LDCD of two airplanes during scheduled maintenance, and a determination that certain compliance times need to be revised. The FAA is issuing this AD to address the unsafe condition on these products.
For the purposes of this AD, an affected part is a frame fork having a part number identified in figure 1 to paragraph (g) of this AD.
This paragraph restates the requirements of paragraph (g) of AD 2018-20-06, with revised compliance language. At the applicable time specified in paragraph (i) of this AD, or before exceeding the threshold defined in figure 2 to paragraph (h) of this AD, whichever occurs later: Do the actions specified in paragraphs (h)(1) through (3) of this AD. Repeat the high frequency eddy current (HFEC) inspection specified in paragraph (h)(3) of this AD at all LDCD frame fork stations having affected parts thereafter at intervals not to exceed the applicable times specified in figure 2 to paragraph (h) of this AD.
(1) A one-time check of the aft LDCD clearances “U” and “V” between the latching hooks and the eccentric bush at frame (FR) 60 through FR64A, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018. If any value outside tolerance is found, adjust the latching hook before further flight, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018.
(2) A one-time detailed inspection to detect signs of wear of the hooks, eccentric bushes, and x-stops, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015. If any wear is found, do all applicable corrective actions before further flight, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015.
(3) An HFEC inspection to detect cracking at all frame fork stations of the aft LDCD, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018. If any crack is found, before further flight, replace the cracked frame fork, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; repair the cracked frame fork, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018; or modify (reinforce) the cracked frame fork, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-52-6085, Revision 01, dated May 2, 2018; except as required by paragraph (j) of this AD.
At the later of the times specified in paragraphs (i)(1) and (2) of this AD, do the actions required by paragraph (h) of this AD.
(1) Before the accumulation of 4,500 total flight cycles.
(2) At the applicable time specified by paragraph (i)(2)(i) or (ii) of this AD.
(i) For airplanes that have accumulated 8,000 or more total flight cycles as of January 26, 2017 (the effective date of AD 2016-25-03, Amendment 39-18729 (81 FR 93801, December 22, 2016) (“AD 2016-25-03”)): Within 100 flight cycles after January 26, 2017.
(ii) For airplanes that have accumulated fewer than 8,000 total flight cycles as of January 26, 2017 (the effective date of AD 2016-25-03): Within 400 flight cycles after January 26, 2017.
Where Airbus Service Bulletin A300-52-6085, Revision 01, dated May 2, 2018, specifies to contact Airbus for appropriate action: Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD.
Accomplishment of corrective actions on an airplane as required by paragraph (h)(1) or (2) of this AD; or repair, modification, or replacement of a frame fork as required by paragraph (h)(3) of this AD, on the aft LDCD of an airplane; does not constitute terminating action for the repetitive HFEC inspections required by paragraph (h)(3) of this AD for that airplane.
Although the Accomplishment Instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; and Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018; specify to submit certain information to the manufacturer, this AD does not include that requirement.
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.
