Airworthiness Directive · Amendment 39-19073 · Fuselage
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD; certificated in any category; except those on which Airbus Modification 5438 was embodied in production.
(1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Model A300 B4-605R and B4-622R airplanes.
(3) Model A300 F4-605R and F4-622R airplanes.
(4) Model A300 C4-605R Variant F airplanes.
(5) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.
We are adopting a new airworthiness directive (AD) for 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 Model A310 series airplanes. This AD was prompted by a report of cracking in the door sill area of the aft cargo door. This AD requires repetitive inspections of the aft cargo door lower torsion box area, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
Within the applicable compliance time specified in table 1 to paragraph (g) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the door sill area (including the sill beam flag, lock fitting, door sill web, and torsion door panel) of the aft cargo door lower torsion box area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin A310-53-2143, dated February 11, 2016; as applicable. Repeat the HFEC inspection thereafter at intervals not to exceed 15,100 flight cycles.
| Airplane configuration | Compliance time |
|---|---|
| Repaired (date known), post-Airbus Modification 10319 lock fittings installed using Airbus Structural Repair Manual (SRM) Task 51-72-00 | Before exceeding 25,800 flight cycles since the lock fitting replacement. |
| Repaired (no record, date unknown), post-Airbus Modification 10319 lock fittings installed using Airbus SRM Task 51-72-00 | Before exceeding 25,800 flight cycles from November 1, 1996. |
| Non-repaired airplane, or airplane repaired with pre-Airbus Modification 10319 lock fittings using Airbus SRM Task 51-72-00 | No inspection required. |
If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin A310-53-2143, dated February 11, 2016; as applicable; except, where Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin A310-53-2143, dated February 11, 2016; specifies to contact Airbus for appropriate action, and specifies that action as “RC” (Required for Compliance), before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (j)(2) of this AD.
Repair of a lock fitting as required by paragraph (h) of this AD constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for the repaired fitting location only. All other post-Airbus Modification 10319 installed fittings are to be inspected as required by paragraph (g) of this AD.
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.
