Airworthiness Directive · Amendment 39-14366 · Airbus Model A300 B4-600 and A300 B4-600R Series Airplanes; and A300 F4-605R and A300 C4-605R Variant F Airplanes
Airbus Model A300 B4-600 and A300 B4-600R Series Airplanes; and A300 F4-605R and A300 C4-605R Variant F Airplanes
Superseded. A later AD replaced this one: AD 2014-20-18. Comply with the one in force.
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; except airplanes on which Airbus Modification 12171 or 12249 has been accomplished or on which Airbus Service Bulletin A300-57-6069 has been accomplished.
The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B4-600 and A300 B4-600R series airplanes, and all Model A300 F4-605R airplanes. That AD currently requires repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of fuselage frame FR47. This new AD revises certain inspection thresholds and intervals. This new AD also adds inspections to detect cracks of additional attachment holes. This AD results from reports of cracks found before the inspection thresholds in the existing AD and cracks found in nearby areas not inspected by the existing AD. We are issuing this AD to prevent fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Perform a rotating probe inspection to detect cracking of the applicable attachment holes on the left and right internal angles of the wing center box in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004. Do the inspection at the applicable time specified by paragraph 1.E.(2), Accomplishment Timescale, of Revision 06 of the service bulletin, except as required by paragraph (m) of this AD. Repeat the rotating probe inspection specified in this paragraph thereafter at intervals not to exceed the applicable interval specified in Revision 06 of the service bulletin, except that all touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections.
(g) If no cracking is found during any inspection required by paragraph (f) of this AD: Prior to further flight, install new fasteners in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004.
(h) If any cracking is found during any inspection required by paragraph (f) of this AD: Prior to further flight, perform applicable corrective actions (including reaming, drilling, drill-stopping holes, chamfering, performing follow-on inspections, and installing new or oversize fasteners) in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004, except as required by paragraph (n) of this AD.
(i) Perform a rotating probe inspection to detect cracking of the applicable attachment holes in the horizontal flange of the internal corner angle fitting of fuselage frame FR47, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002. Do the inspection at the applicable time specified in paragraph 1.E., Compliance, of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002, except as provided by paragraph (m) of this AD; or within 1,500 flight cycles after July 8, 2002 (the effective date of AD 2002-11-04, amendment 39-12765); whichever occurs later. Repeat the rotating probe inspection specified in this paragraph thereafter at intervals not to exceed the applicable interval specified in Airbus Service Bulletin A300-57-6086, dated June 6, 2000, except that all touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections.
(j) If no cracking is found during any inspection required by paragraph (i) of this AD: Prior to further flight, install new fasteners in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002.
(k) If any cracking is found during any inspection required by paragraph (i) of this AD: Prior to further flight, perform applicable corrective actions (including inspecting hole T if any cracking is found at hole G, reaming the holes, and installing oversize fasteners) in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002, except as required by paragraph (n) of this AD.
Modify the left and right internal angle fittings of the wing center box. The modification includes performing a rotating probe inspection to detect cracking, repairing cracks, cold expanding holes, and installing medium interference fitting bolts. Perform the modification in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001; and at the applicable time specified by paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 2001; except as required by paragraphs (m) and (n) of this AD.
Where the service bulletins specified in paragraphs (f), (i), and (l) of this AD specify a grace period relative to receipt of the service bulletin, this AD requires compliance within the applicable grace period following the effective date of this AD, if the threshold has been exceeded.
(n) If any crack is detected during any inspection required by this AD, and the applicable service bulletin specifies to contact the manufacturer for disposition of certain corrective actions: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).
Actions accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A300-57-6086, dated June 6, 2000, are acceptable for compliance with the requirements of paragraph (i) of this AD.
(p) Modifications accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000; are acceptable for compliance with the requirements of paragraph (l) of this AD.
Although Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004; and Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002; 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.
