Airworthiness Directive · Amendment 39-16029 · Fuselage
Airbus Model A310-203 and -222 Airplanes and Model A300 B4-620 Airplanes
This AD applies to Airbus Model A310-203 and -222 airplanes, and Model A300 B4-620 airplanes; certificated in any category; all serial numbers except airplanes on which Airbus Modification 05526 has been incorporated in production.
We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions.
(1) Except as required by paragraph (f)(2) of this AD: Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later, modify the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame 80/82 and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus Mandatory Service Bulletin A310-53-2025, Revision 06, dated August 3, 2006; as applicable. Do all applicable related investigative and corrective actions before further flight.
(2) For airplanes identified in paragraph (c) of AD 2006-22-03, amendment 39-14800: At the earlier of the compliance times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions specified in paragraph (f)(1) of this AD.
(i) Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later.
(ii) At the compliance time specified in paragraph (h) of AD 2006-22-03.
(3) For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done after the accumulation of 6,000 total flight cycles since first flight: At the times specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an eddy current inspection for any cracking in the critical area of the rear pressure bulkhead between stringers 8 and 18, and repair all cracking before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-6005, Revision 04, dated July 18, 2007; or Airbus Mandatory Service Bulletin A310-53-2024, Revision 05, dated October 13, 2006; as applicable.
(i) Before or concurrently with the modification required by paragraph (f)(1) or (f)(2) of this AD, as applicable; and
(ii) Before the accumulation of 18,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 9,000 flight cycles.
Note 1: For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done at or before the accumulation of 6,000 total flight cycles since first flight: No action is required by this AD. For these airplanes, refer to Airbus A300-600 ALI Task 531919-01-1A or Airbus A310 ALI Task 531919-01-1A, as applicable, for guidance on the normal inspection program.
(4) Modifications done before the effective date of this AD in accordance with the service bulletins identified in Table 1 of this AD are acceptable for compliance with the requirements of paragraph (f)(1) and (f)(2) of this AD.
| Model— | Airbus Service Bulletin— | Revision— | Dated— |
|---|---|---|---|
| A300 B4-620 airplanes | A300-53-6006 | Original | May 6, 1986. |
| A300-53-6006 | 1 | September 19, 1986. | |
| A300-53-6006 | 2 | August 11, 1988. | |
| A310-203 and -222 airplanes | A310-53-2025 | Original | April 21, 1986. |
| A310-53-2025 | 1 | September 19, 1986. | |
| A310-53-2025 | 2 | February 16, 1987. | |
| A310-53-2025 | 3 | April 7, 1987. | |
| A310-53-2025 | 4 | October 20, 1987. | |
| A310-53-2025 | 5 | March 24, 1989. |
(5) Inspections done before the effective date of this AD in accordance with the service bulletins identified in Table 2 of this AD are acceptable for compliance with the requirements of paragraph (f)(3) of this AD.
| Model— | Airbus Service Bulletin— | Revision— | Dated— |
|---|---|---|---|
| A300 B4-620 airplanes | A300-53-6005 | Original | May 6, 1986. |
| A300-53-6005 | 1 | June 20, 1986. | |
| A300-53-6005 | 2 | September 22, 1986. | |
| A300-53-6005 | 3 | April 22, 1987. | |
| A310-203 and -222 airplanes | A310-53-2024 | Original | April 21, 1986. |
| A310-53-2024 | 1 | June 20, 1986. | |
| A310-53-2024 | 2 | October 2, 1986. | |
| A310-53-2024 | 3 | February 17, 1987. | |
| A310-53-2024 | 4 | February 2, 1988. |
(6) Modification of the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82 in accordance with paragraph (h) of AD 2006-22-03 is acceptable for compliance with the corresponding requirement of paragraphs (f)(1) and (f)(2) of this AD.
Note 2: This AD differs from the MCAI and/or service information as follows. This AD includes a compliance time specified in paragraph (f)(2) of this AD for airplanes that are also affected by AD 2006-22-03. We realize that the requirements of this AD will necessitate that some operators do the modification required by paragraph (h) of AD 2006-22-03 early. However, accomplishing the modification within the compliance time specified in this AD is required to address cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead.
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.
