Airworthiness Directive · Amendment 39-18348 · Wings
Airbus Airplanes
(1) This AD applies to the airplanes identified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category, except as provided by paragraph (c)(2) of this AD.
(i) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all serial numbers, except those on which Airbus modification 55306 or 55792 has been embodied in production.
(ii) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes, all serial numbers, except those on which Airbus modification 55306 or 55792 has been embodied in production.
(2) This AD does not apply to Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes on which the repair specified in Airbus Repair Drawing R57115053, R57115051, or R57115047 (installation of titanium doubler on both sides) has been accomplished. AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June 6, 2007), applies to these airplanes.
We are superseding Airworthiness Directive (AD) 2011-24-05 for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes, and Model A340- 200 and -300 series airplanes. AD 2011-24-05 required repetitive inspections for cracking of the hole(s) of the horizontal flange of the keel beam, and repair if necessary. This new AD requires changing the inspection compliance times, and, for certain airplanes, adding a one- time ultrasonic inspection for cracking at a certain fastener hole. This new AD also provides optional terminating action for the repetitive inspections. This AD was prompted by a determination that the rototest inspection and applicable corrective actions of a certain fastener hole were inadvertently omitted from the requirements in AD 2011-24-05. We are issuing this AD to detect and correct cracking of the fastener holes, which could result in rupture of the keel beam, and consequent reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (n) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), with new service information and revised credit for certain actions. At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do an NDT inspection of the hole(s) of the horizontal flange of the keel beam located on frame (FR) 40 datum on the right-hand (RH) and/or left-hand (LH) side of the fuselage, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD. Accomplishing an inspection required by paragraph (j) of this AD terminates the inspections required by this paragraph.
(1) For airplanes on which an inspection required by paragraph (h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), has not been done as of January 3, 2012 (the effective date of AD 2011-24-05): At the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) For all airplanes except those identified in paragraph (g)(1)(ii) of this AD: Within the “Mandatory Threshold” (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later. The compliance times for configurations 02 through 06 specified in the “Mandatory Threshold” column in table 1 of paragraph 1.E., “Compliance,” are total flight cycles and total flight hours.
(ii) For Model A330-201, -202, -203, -223, -243, -301, -321, -322, -323, -341, -342, and -343 airplanes, except those on which Airbus modification 49202 has been embodied in production, or Airbus Service Bulletin A330-57-3090 has been embodied in service; and Model A340-200 and -300 series airplanes, except those on which Airbus modification 49202 has been embodied in production or Airbus Service Bulletin A340-57-4098 has been embodied in service, and except Model A340-211, -212, -213, -311, -312, and -313 airplanes on which the repair specified in Airbus Repair Drawing R57115053, R57115051, or R57115047 has been accomplished: At the earlier of the times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD.
(A) Within the “Mandatory Threshold” (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006; depending on the configuration of the aircraft model; or within 3 months after September 13, 2007 (the effective date of AD 2007-16-02, Amendment 39-15141 (72 FR 44731, August 9, 2007)), whichever occurs later. The compliance times for Model A330 post-mod. 41652 and pre-mod. 44360, post-mod. 44360, and pre-mod. 49202 (as specified in Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006); and Model A340 post-mod. 41652, post-mod. 43500 and pre-mod. 44360, post-mod. 44360 and pre-mod. 49202, and weight variant 027 (as specified in Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006); specified in the “Mandatory Threshold” column in table 1 of paragraph 1.E., “Compliance,” are total flight cycles and total flight hours.
(B) Within the “Mandatory Threshold” (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later. The compliance times for configurations 02 through 06 specified in the “Mandatory Threshold” column in table 1 of paragraph 1.E., “Compliance,” are total flight cycles and total flight hours.
(2) For airplanes on which an inspection required by paragraph (h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), has been done as of January 3, 2012 (the effective date of AD 2011-24-05): At the earlier of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within the “Mandatory Intervals” given in table 1 of paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006; as applicable.
(ii) Within the applicable “Mandatory Interval” specified in table 1 of Paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later.
(3) Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011.
(4) Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012.
(5) Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011.
(6) Airbus Service Bulletin A340-57-4089, Revision 05, dated November 13, 2012.
This paragraph restates the requirements of paragraph (p) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). If no cracking is found during any inspection required by paragraph (g) of this AD, do the actions required by paragraphs (h)(1) and (h)(2) of this AD.
(1) Before further flight: Install a new or oversized fastener, as applicable; seal the fastener; and do all other applicable actions; in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD.
(2) Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed the “Mandatory Intervals” specified in Paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable.
(1) This paragraph restates the requirements of paragraph (o) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), with revised method of compliance language. If any cracking is found during any inspection required by paragraph (g) of this AD, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(2) This paragraph restates the requirements of paragraph (r) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), with new service information and revised method of compliance language. Modifying the fastener installation in the junction keel beam fitting at FR 40, as specified in paragraph (i)(2)(i), (i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as applicable, terminates the requirements of paragraphs (g) and (h) of this AD; except, for airplanes on which a crack was detected at hole 5 before oversizing of the keel beam, in accordance with step 3.B.(1)(b) 3 of the Accomplishment Instructions of Airbus Service Bulletin A330-57-3098, dated August 30, 2007; or Airbus Service Bulletin A340-57-4106, dated August 30, 2007; or in accordance with step 3.C.(2)(c) of the Accomplishment Instructions of Airbus Service Bulletin A330-57-3098, Revision 03, dated September 24, 2012, or Airbus Service Bulletin A340-57-4106, Revision 03, dated September 24, 2012; before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. In case of any crack finding during any modification specified in this paragraph: Where the service information specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(i) Modification in accordance with Airbus Service Bulletin A330-57-3098, dated August 30, 2007, before January 3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)).
(ii) Modification in accordance with Airbus Service Bulletin A330-57-3098, Revision 03, dated September 24, 2012, before the effective date of this AD.
(iii) Modification in accordance with Airbus Service Bulletin A340-57-4106, dated August 30, 2007, before January 3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)).
(iv) Modification in accordance with Airbus Service Bulletin A340-57-4106, Revision 03, dated September 24, 2012, before the effective date of this AD.
At the applicable times specified in paragraphs (j)(1) and (j)(2) of this AD: Do a rotating probe inspection for cracking of the fastener hole(s) of the horizontal flange of the keel beam located on FR 40 datum on the RH and LH side of the fuselage, as applicable to airplane type and depending on airplane configuration and utilization, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, dated November 13, 2012; as applicable. Repeat the inspection thereafter at intervals not to exceed the “Mandatory Intervals” specified in Paragraph 1.E.(2) of the Accomplishment Timescale of Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, dated November 13, 2012; as applicable. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD.
(1) For airplanes on which the inspection required by paragraph (g) of this AD has not been done as of the effective date of this AD: Do the inspection before exceeding the applicable compliance times specified in the “Mandatory Threshold” column of the tables in paragraph 1.E.(2) of the Accomplishment Timescale of Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, dated November 13, 2012; as applicable; or within 12 months after the effective date of this AD; whichever occurs later.
(2) For airplanes on which the inspection required by paragraph (g) of this AD has been done as of the effective date of this AD: Do the inspection within the applicable compliance times specified in the “Mandatory Interval” column of the tables in paragraph 1.E.(2) of the Accomplishment Timescale of Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, dated November 13, 2012; as applicable; or within 12 months after the effective date of this AD; whichever occurs later.
