Airworthiness Directive · Amendment 39-11612 · Airbus Model A300-600 and A310 Series Airplanes
Airbus Model A300-600 and A310 Series Airplanes
Model A300-600 and A310 series airplanes, certificated in any category, on which Airbus Modification 06925 has been accomplished in production; except airplanes on which Airbus Modification 08907 has been accomplished.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus A300-600 and A310 series airplanes, that requires repetitive high frequency eddy current (HFEC) inspections to detect cracking of the inner flange of fuselage frame FR73A, between beams 5 and 7, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the inner flange of fuselage frame FR73A, which could result in reduced structural integrity of the fuselage.
To detect and correct fatigue cracking of the inner flange of fuselage frame FR73A, which could result in reduced structural integrity of the fuselage, accomplish the following:
(a) Prior to the accumulation of 18,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current (HFEC) inspection to detect cracking of the inner flange (left and right sides) of the rear fuselage frame FR73A, between beams 5 and 7, in accordance with Airbus Service Bulletin A310-53-2107, Revision 01 (for Model A310 series airplanes), or A300-53-6116, Revision 01 (for Model A300-600 series airplanes); both dated July 2, 1999; as applicable.
(1) If no crack is detected, repeat the HFEC inspection thereafter at intervals not to exceed 5,000 flight cycles.
(2) For any crack that is less than or equal to 0.20 inch (5.0 millimeters) in length: Prior to further flight, accomplish either paragraph (a)(2)(i) or (a)(2)(ii) of this AD.
(i) Rework the frame in accordance with the applicable service bulletin. Within 3,000 flight cycles after accomplishing the rework, replace the fuselage frame FR73A between beams 5 and 7 with a new frame section in accordance with the applicable service bulletin. Or
(ii) Replace the fuselage frame FR73A between beams 5 and 7 with a new frame section, in accordance with the applicable service bulletin.
(3) For any crack greater than 0.20 inch (5.0 millimeters) in length: Prior to further flight, accomplish either paragraph (a)(3)(i) or (a)(3)(ii) of this AD.
(i) Repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent). Or
(ii) Replace the fuselage frame FR73A between beams 5 and 7 with a new section, in accordance with the applicable service bulletin.
(b) Within 18,000 flight cycles after any replacement accomplished in accordance with paragraph (a)(2)(i), (a)(2)(ii), or (a)(3)(ii) of this AD: Repeat the inspection specified by paragraph (a) of this AD. Thereafter, repeat the inspection at intervals not to exceed 5,000 flight cycles.
(c) Submit a report of inspection findings (both positive and negative) of any inspection required by this AD to Airbus Industrie, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; at the applicable time specified in paragraph (c)(1) or (c)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, the age of the airplane since entry into service, and the number of landings and flight hours on the airplane. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.
(1) For airplanes on which the inspection required by paragraph (a) of this AD is accomplished after the effective date of this AD: Submit the report within 10 days after performing the inspection.
(2) For airplanes on which the inspection required by paragraph (a) of this AD has been accomplished prior to the effective date of this AD: Submit the report within 10 days after the effective date 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.
