Airworthiness Directive · Amendment 39-14412 · Airbus Model A300 B2 Series Airplanes, Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model A310-300 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Airbus Model A300 B2 Series Airplanes, Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model A310-300 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; Model A300 C4-605R Variant F airplanes; Model A310-203, -204, -221, and -222 airplanes; and Model A310-304, -322, -324, and -325 airplanes; certificated in any category; except for airplanes on which Airbus Modification 12662 has been done in production.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus transport category airplanes. This AD requires repetitive eddy current inspections for cracks of the stiffener fittings of the fuselage at frame (FR) 12A, and corrective actions if necessary. This AD also provides a terminating action for the inspections. This AD results from reports of cracks on the upper attachment fitting of the stiffener fitting at FR12A. We are issuing this AD to prevent failure of the stiffener fittings, which could result in the reduced structural integrity of the floor and rods around FR 12A.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the applicable initial inspection threshold specified in Table 1 of this AD or within the applicable grace period specified in Table 2 of this AD, whichever occurs later: Do an eddy current inspection for cracks of the stiffener fittings of the fuselage at FR 12A, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0365, Revision 01 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-203 airplanes); Airbus Service Bulletin A300-53-6138, Revision 01 (for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes); or Airbus Service Bulletin A310-53-2117, Revision 01 (for Model A310-203, -204, -221, and -222 airplanes, and Model A310-304, -322, -324, and -325 airplanes); all dated April 4, 2005; as applicable. Repeat the inspection thereafter at intervals not to exceed the applicable compliance time specified in Table 1 of this AD until the actions specified in paragraph (h) of this AD are done.
| For airplanes identified as— | Do the initial inspection prior to the accumulation of— | And repeat at intervals not to exceed— |
|---|---|---|
| Configuration 01 in Airbus Service Bulletin A300-53-0365, Revision 01, dated April 4, 2005 | 19,300 total flight cycles | 11,450 flight cycles. |
| Configuration 02 in Airbus Service Bulletin A300-53-0365, Revision 01, dated April 4, 2005 | 15,500 total flight cycles | 9,200 flight cycles. |
| Configuration 01 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 | 19,300 total flight cycles | 11,450 flight cycles. |
| Configuration 02 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 | 17,600 total flight cycles | 11,450 flight cycles. |
| Configuration 03 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 | 12,700 total flight cycles | 8,000 flight cycles. |
| Configuration 04 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 | 10,200 total flight cycles | 6,400 flight cycles. |
| Configuration 01 in Airbus Service Bulletin A310-53-2117, Revision 01, dated April 4, 2005 | 19,300 total flight cycles | 11,450 flight cycles. |
| Configuration 02 in Airbus Service Bulletin A310-53-2117, Revision 01, dated April 4, 2005 | 17,600 total flight cycles | 11,450 flight cycles. |
| Configuration 03 in Airbus Service Bulletin A310-53-2117, Revision 01, dated April 4, 2005 | 12,700 total flight cycles | 8,000 flight cycles. |
| For Airbus Model— | Grace period is— |
|---|---|
| A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes | Within 2,500 flight cycles after the effective date of this AD. |
| A300 B4-2C, B4-103, and B4-203 airplanes; A300 B4-601, B4-603, B4-620, and B4-622 airplanes; A300 B4-605R and B4-622R airplanes; A300 F4-605R and F4-622R airplanes; A300 C4-605R Variant F airplanes; A310-203, -204, -221, and -222 airplanes; and A310-304, -322, -324, and -325 airplanes | Within 2,000 flight cycles after the effective date of this AD. |
If any cracking is found during any inspection required by paragraph (f) of this AD, before further flight, do the replacement and installation specified in paragraph (h) of this AD.
Replacing the existing fitting on FR12A with a FR12A crossbeam and installing a new web between FR12A and FR13 at stringer 26 in accordance with Airbus Service Bulletin A300-53-0364, Revision 02, dated September 24, 2004 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-203 airplanes); Airbus Service Bulletin A300-53-6137, Revision 03, dated April 4, 2005 (for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes); or Airbus Service Bulletin A310-53-2116, Revision 02, dated September 24, 2004 (for Model A310-203, -204, -221, and -222 airplanes, and Model A310-304, -322, -324, and -325 airplanes); as applicable; and except as required by paragraph (i) of this AD; constitutes terminating action for the requirements of this AD.
(i) Where the service bulletins specify to contact the manufacturer for certain information, before further flight, do the terminating action according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent).
Actions accomplished before the effective date of this AD according to the Airbus service bulletins specified in Table 3 of this AD are considered acceptable for compliance with the corresponding actions specified in this AD.
| Airbus Service Bulletin | Revision level | Date |
|---|---|---|
| A300-53-0364 | Original | December 1, 2003. |
| A300-53-0364 | 01 | May 5, 2004. |
| A300-53-0365 | Original | December 1, 2003. |
| A300-53-6137 | Original | December 1, 2003. |
| A300-53-6137 | 01 | May 5, 2004. |
| A300-53-6137 | 02 | September 24, 2004. |
| A300-53-6138 | Original | December 1, 2003. |
| A310-53-2116 | Original | December 1, 2003. |
| A310-53-2116 | 01 | May 5, 2004. |
| A310-53-2117 | Original | December 1, 2003. |
Although the service bulletins referenced in this AD 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.
