Airworthiness Directive · Amendment 39-17991 · Wings
Airbus Airplanes
This AD applies to Airbus Model 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 embodied in production, or on which Airbus Service Bulletin A300-57-6069 has been embodied in service.
We are superseding Airworthiness Directive (AD) 2005-23-08 for certain Airbus Model A300 B4-605R and B4-622R airplanes; Model A300 F4- 605R airplanes; and Model A300 C4-605R Variant F airplanes. AD 2005-23- 08 required 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 adds new repetitive ultrasonic inspections for cracks of the center wing box lower panel; and repair if necessary. This new AD also removes certain airplanes from the applicability. This AD was prompted by reports of cracks found on the horizontal flange of the Frame 47 internal corner angle fitting while accomplishing the modification required by AD 2005-23-08. We are issuing this AD to detect and correct 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.
This paragraph restates the requirements of paragraphs (f), (g), and (h) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005), with revised service information. 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; or Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006. Do the inspection at the applicable time specified by paragraph 1.E.(2), Accomplishment Timescale, of Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004; except as required by paragraph (j) of this AD. Repeat the rotating probe inspection specified in this paragraph thereafter at intervals not to exceed the applicable interval specified in Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 2004, except that all touch-and-go landings must be counted in determining the total number of flight cycles between consecutive inspections. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.
(1) If no cracking is found during any inspection required by paragraph (g) 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; or Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.
(2) If any cracking is found during any inspection required by paragraph (g) 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; or Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006; except as required by paragraph (k) of this AD. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006, may be used to accomplish the actions required by this paragraph.
This paragraph restates the requirements of paragraphs (i), (j), and (k) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005), with revised service information. 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; or Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012. 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 (j) of this AD; or within 1,500 flight cycles after July 8, 2002 (the effective date of AD 2002-11-04, Amendment 39-12765 (67 FR 38193, June 3, 2002)); 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. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.
(1) If no cracking is found during any inspection required by paragraph (h) 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; or Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.
(2) If any cracking is found during any inspection required by paragraph (h) 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; or Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012; except as required by paragraph (k) of this AD. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, may be used to accomplish the actions required by this paragraph.
This paragraph restates the requirements of paragraph (l) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). 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 (j) and (k) of this AD.
This paragraph restates the requirements of paragraph (m) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). Where the service information specified in paragraphs (g), (h), and (i) of this AD specify a grace period relative to receipt of the service bulletin, this AD requires compliance within the applicable grace period following December 19, 2005 (the effective date of AD 2005-23-08), if the threshold has been exceeded.
This paragraph restates the requirements of paragraph (n) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). If any crack is detected during any inspection required by paragraph (g), (h), or (i) of this AD, and the applicable service information specifies to contact the manufacturer for disposition of certain corrective actions: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).
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.
