AD 2011-24-05

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 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: Do the actions required by paragraphs (h), (l), and (m) of this AD.

(h) For airplanes identified in paragraph (g) of this AD, within the mandatory threshold (flight cycles or flight hours) mentioned in the paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02; or A330-57-3081, including Appendix 01, Revision 02; both 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 (72 FR 44731, August 9, 2007)); whichever occurs later: Carry out the NDT (non-destructive test) inspection of the hole(s) of the horizontal flange of the keel beam located on FR 40 datum on RH (right-hand) and/or LH (left-hand) side of the fuselage, in accordance with the instructions of the applicable service bulletin listed in table 1 of this AD. After the effective date of this AD, use only 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. Inspection in accordance with Airbus A330/A340 200-300 Technical Disposition F57D03012810, Issue B, dated August 18, 2003; or Airbus A330/A340 Technical Disposition 582.0651/2002, Issue A, dated October 17, 2002; satisfies the inspection requirements for the first rotating probe inspection which is specified at the inspection threshold of this AD. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph of this AD.

Note 1: In order to prevent large repairs or heavy maintenance, Airbus recommends to perform the above inspection according to recommended thresholds mentioned in paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02; or Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02; both dated January 24, 2006.

(i) In case of any crack finding during the inspection required by paragraph (h) of this AD, before further flight, contact Airbus in order to get repair instructions before next flight, and repair before further flight.

(j) Should no crack be detected during the inspection required by paragraph (h) of this AD:

(1) Before further flight: Follow up the actions indicated in the flow charts, Figure 7, 8, or 9, of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006, or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; or Figure 5, 6, or 7, of Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006, or Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; in accordance with the instructions of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006, or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006, or Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; as applicable.

(2) Within 30 days after September 13, 2007, or within 30 days after doing the inspection required by paragraph (h) of this AD, whichever occurs later: Send the report of actions carried out in paragraph (j)(1) of this AD to Airbus.

(3) Renew the inspection at mandatory intervals given in 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; in accordance with the instructions of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006, or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006, or Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; and send the inspection results to Airbus. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph of this AD.

Note 2: In order to prevent large repairs or heavy maintenance, Airbus recommends to perform the above repetitive inspection according to recommended intervals mentioned in 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.

(k) Upon detection of a crack during a repetitive inspection required by paragraph (j)(3) of this AD, before further flight, contact Airbus to get repair instructions, and repair before further flight.

(l) For airplanes identified in paragraph (g) of this AD: No additional work is required for compliance with paragraph (h) of this AD for aircraft on which the inspection specified in Airbus Service Bulletin A330-57-3081, dated October 30, 2003, or Revision 01, dated May 18, 2004; or Airbus Service Bulletin A340-57-4089, dated October 30, 2003, or Revision 01, dated March 2, 2004, has been accomplished. Nevertheless, the operators must check that their inspection program is in accordance with 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; for the repetitive inspection.

(m) For airplanes identified in paragraph (g) of this AD on which Airbus Modification 41652 is not embodied: When the aircraft has been modified in accordance with Airbus Service Bulletin A330-57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-57-4098, dated March 27, 2006; as applicable; the repetitive inspections required by this AD are cancelled. In case of any crack finding during the modification: Where the applicable service bulletin specifies to contact Airbus, before further flight, contact Airbus to get repair instructions, and repair.

At the applicable time in paragraph (n)(1) or (n)(2) of this AD: Do an NDT inspection of the hole(s) of the horizontal flange of the keel beam located on FR 40 datum on RH and/or LH side of the fuselage, in accordance with the Accomplishment Instructions 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. Inspection in accordance with Airbus A330/A340 200-300 Technical Disposition F57D03012810, Issue B, dated August 18, 2003; or Airbus A330/A340 Technical Disposition 582.0651/2002, Issue A, dated October 17, 2002; is acceptable for compliance with the inspection requirements for the first rotating probe inspection required by this paragraph. Doing the inspection required by this paragraph terminates the requirements of paragraphs (h) and (j)(3) of this AD.

(1) For airplanes on which an inspection required by paragraph (h) of this AD has not been done as of the effective date of this AD: At the applicable time specified in paragraph (n)(1)(i) or (n)(1)(ii) of this AD.

(i) For all airplanes except those identified in paragraph (g) of this AD: Within the “Mandatory Threshold” (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of the Accomplishment Instructions 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 the effective date of this AD; 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 airplanes identified in paragraph (g) of this AD: At the earlier of the times specified in paragraphs (n)(1)(ii)(A) and (n)(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; whichever occurs later. The compliance times for Model A330 post-mod. No. 41652 and pre-mod. No. 44360, post-mod. No. 44360, and pre-mod. No. 49202 (specified in Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006); and Model A340 post-mod. No. 41652, post-mod. No. 43500 and pre-mod. No. 44360, post-mod. No. 44360 and pre-mod. No. 49202, and Weight Variant 027 (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 the Accomplishment Instructions 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 the effective date of this AD; 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 this AD has been done as of the effective date of this AD: At the earlier of the times specified in paragraphs (n)(2)(i) and (n)(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 the effective date of this AD; whichever occurs later.

Note 3: To prevent large repairs or heavy maintenance, Airbus recommends to perform the above inspection according to recommended thresholds 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.

(o) If any cracking is found during any inspection required by paragraph (n) of this AD, before further flight, repair in accordance with a method approved by the International Branch, ANM-116, Transport Airplane Directorate, FAA, or European Aviation Safety Agency (EASA) (or its delegated agent).

(p) If no cracking is found during any inspection required by paragraph (n) of this AD, do the actions required by paragraphs (p)(1) and (p)(2) of this AD.

(1) Before further flight: Install new or oversized fastener, as applicable; seal the fastener; and do all other applicable actions; in accordance with the Accomplishment Instructions 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.

(2) Repeat the inspection required by paragraph (n) 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.

Note 4: To prevent large repairs or heavy maintenance, Airbus recommends to perform the above repetitive inspection according to recommended intervals mentioned 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.

Inspections done before the effective date of this AD in accordance with the service information specified in table 2 of this AD are acceptable for compliance with the corresponding inspection required by paragraph (n) of this AD.

(r) Modifying the fasteners installation in the junction keel beam fitting at FR 40, in accordance with Airbus Service Bulletin A330-57-3098, dated August 30, 2007; or Airbus Service Bulletin A340-57-4106, dated August 30, 2007; as applicable; before the effective date of this AD terminates the requirements 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), before further flight, repair in accordance with a method approved by the International Branch, ANM-116, Transport Airplane Directorate, FAA, or EASA (or its delegated agent).

(s) Modifying the fasteners installation in the junction keel beam fitting at FR 40, in accordance with Airbus Service Bulletin A330-57-3098, excluding Appendix 1, Revision 01, dated July 31, 2009; or Airbus Service Bulletin A340-57-4106, excluding Appendix 1, Revision 01, dated July 31, 2009; as applicable; terminates the requirements of this AD.

(t) Modifying the fasteners installation in the junction keel beam fitting at FR 40, in accordance with Airbus Service Bulletin A330-57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-57-4098, dated March 27, 2006; as applicable; terminates the requirements of this AD.

(u) In case of any crack finding during any modification specified paragraphs (r), (s), and (t) of this AD: Where the applicable service bulletin specifies to contact Airbus, before further flight, repair in accordance with a method approved by the International Branch, FAA, or EASA (or its delegated agent).

Note 5: This AD differs from the MCAI and/or service information as follows: No differences.