Airworthiness Directive · Amendment 39-15787 · Airbus Model A300, A310, and A300-600 Series Airplanes
Airbus Model A300, A310, and A300-600 Series Airplanes
This AD applies to Airbus airplanes identified in Table 1 of this AD, certificated in any category.
| Model— | As identified in Airbus Mandatory Service Bulletin— |
|---|---|
| (1) A300 series airplanes | A300-57-0232, Revision 02, dated February 21, 2000. |
| (2) A310 series airplanes | A310-57-2075, Revision 03, dated December 1, 2006. |
| (3) A300-600 series airplanes | A300-57-6079, Revision 04, dated February 21, 2000. |
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300, A310, and A300-600 series airplanes. That AD currently requires repetitive detailed visual inspections to detect cracks in the pylon thrust and sideload fitting of the wing, and replacement of any cracked pylon thrust and sideload fitting with a new fitting. This new AD reduces the threshold and repetitive intervals for the detailed inspection for certain airplanes and reduces the applicability of the existing AD. This AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 98-16-11:
At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Perform a detailed inspection to detect cracks in the pylon thrust and sideload fitting of the wing, in accordance with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraph (h) of this AD.
(1) For Model A300 and A300-600 series airplanes: Inspect prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998 (the effective date AD 98-16-11), whichever occurs later, and thereafter at intervals not to exceed 2,800 flight cycles.
(2) For Model A310 series airplanes: Inspect at the earlier of the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this AD. Repeat thereafter at the applicable intervals specified in Table 3 of this AD.
(i) Prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998, whichever occurs later.
(ii) At the applicable time specified in Table 2 of this AD.
| Compliance time (whichever occurs later) | Threshold | Grace period |
|---|---|---|
| A310-200 series airplanes. | Before the accumulation of 1,500 total flight cycles or 3,000 total flight hours since first flight, whichever occurs first | Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. |
| A310-300 series airplanes (short range) | Before the accumulation of 1,300 total flight cycles or 3,800 total flight hours since first flight, whichever occurs first | Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. |
| A310-300 series airplanes (long range) | Before the accumulation of 800 total flight cycles or 4,000 total flight hours since first flight, whichever occurs first | Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. |
| For Model— | Repeat the detailed inspection at the later of— | And, thereafter at intervals not to exceed— |
|---|---|---|
| A310-200 series airplanes. | Within 1,500 flight cycles or 3,000 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first | 1,500 flight cycles or 3,000 flight hours, whichever occurs first. |
| A310-300 series airplanes (short range) | Within 1,300 flight cycles or 3,800 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first | 1,300 flight cycles or 3,800 flight hours, whichever occurs first. |
| A310-300 series airplanes (long range) | Within 800 flight cycles or 4,000 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first | 800 flight cycles or 4,000 flight hours, whichever occurs first. |
If any crack is detected during any inspection required by paragraph (f) of this AD, prior to further flight, replace the pylon thrust and sideload fitting with a new fitting in accordance with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraphs (h) and (j) of this AD.
For all airplanes: As of the effective date of this AD, use only the Accomplishment Instructions of the applicable service bulletin specified in Table 4 of this AD to do the repetitive detailed inspections required by paragraph (f) of this AD and the replacement required by paragraph (g) of this AD.
| Airbus mandatory Service Bulletin— | For model— |
|---|---|
| (1) A300-57-0232, Revision 02, dated February 21, 2000 | A300 series airplanes. |
| (2) A300-57-6079, Revision 04, dated February 21, 2000 | A300-600 series airplanes. |
| (3) A310-57-2075, Revision 03, dated December 1, 2006 | A310 series airplanes. |
(i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300-57-6079, Revision 02, dated January 12, 1998, or Revision 03, dated October 25, 1999 (for Model A300-600 series airplanes); A310-57-2075, Revision 01, dated January 12, 1998, or Revision 02, dated February 21, 2000 (for Model A310 series airplanes); or A300-57-0232, Revision 01, dated January 12, 1998 (for Model A300 series airplanes); are acceptable for compliance with the corresponding requirements of this AD.
Repairing the pylon thrust and sideload fitting of the wing, using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA), or its delegated agent, is acceptable for compliance with the replacement 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.
