Airworthiness Directive · Amendment 39-14437 · Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes, and C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Airbus Model A310-200 and A310-300 Series Airplanes
Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes, and C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Airbus Model A310-200 and A310-300 Series Airplanes
This AD applies to all airplanes identified in Table 1 of this AD, certificated in any category.
| Airbus model | As identified in Airbus Service Bulletin— |
|---|---|
| A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes | A300-53-0363, Revision 01, dated June 10, 2005. |
| A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes | A300-53-6136, Revision 01, dated July 18, 2005. |
| A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes | A310-53-2114, Revision 01, dated September 1, 2005. |
The FAA is superseding an existing airworthiness directive (AD) that applies to certain Airbus Model A300-600 and A310 series airplanes. That AD currently requires repetitive visual inspections to detect corrosion on the lower rim area of the fuselage rear pressure bulkhead; and follow-on actions, if necessary. This new AD requires new repetitive inspections for corrosion on the rear pressure bulkhead between stringer (STGR) 27 (right hand) and STGR27 (left hand), and related investigative and corrective actions if necessary. This AD also requires sending a report of certain information to the manufacturer. The AD also adds airplanes to the applicability of the existing AD. This AD results from findings of severe corrosion on airplanes previously inspected in accordance with the existing AD. We are issuing this AD to detect and correct corrosion at the lower rim area of the fuselage rear pressure bulkhead, which could result in reduced structural integrity of the bulkhead, and consequent decompression of the cabin.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For the purposes of this AD, the term “service bulletin” means the accomplishment instructions of the applicable service bulletin identified in Table 1 of this AD.
Within 60 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness; or within 18 months after the effective date of this AD; whichever is later: Do the detailed inspection, special detailed inspections, and any applicable eddy current and x-ray inspection, for corrosion on the rear pressure bulkhead between stringer (STGR) 27 (right hand) and STGR27 (left hand) in accordance with the service bulletin, and repeat these inspections thereafter at intervals not to exceed 36 months. Do any applicable related investigative and corrective actions before further flight in accordance with the service bulletin, except as provided by paragraph (h) of this AD.
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
Note 2: For the purposes of this AD, a special detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. The examination is likely to make extensive use of specialized inspection techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required.”
(h) If any corrosion damage or crack is found during any inspection or corrective action required by this AD, and the service bulletin recommends contacting Airbus for repair instructions: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA.
(i) Submit a report of corrosion found during the inspections required by paragraph (g) of this AD to SE-A21, Airbus Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the inspection type, a description of any corrosion found, the airplane serial number, and the number of landings and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
Actions done before the effective date of this AD in accordance with Airbus Service Bulletins A300-53-0363, dated October 27, 2004; A300-53-6136, dated October 27, 2004; or A310-53-2114, dated October 27, 2004; as applicable; are acceptable for compliance with the requirements of 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.
