Airworthiness Directive · Amendment 39-17287 · 57: fuselage, wings
Airbus Airplanes
This AD applies to Airbus airplanes, certificated in any category, as identified in paragraphs (c)(1) and (c)(2) of this AD. For airplanes on which Airbus Service Bulletin A300-53-0297 or A300-57-6053 (Airbus Modification 10453), as applicable, has been incorporated as a corrective action (repair following crack finding), no action is required by this AD.
(1) Model A300 B4-2C, B4-103, and B4-203 airplanes, all serial numbers, modified preventively in service (without any preliminary crack findings), as specified in Airbus Service Bulletin A300-53-0297 (Airbus Modification 10453).
(2) Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes, all serial numbers, modified preventively in service (without any preliminary crack findings), as specified in Airbus Service Bulletin A300-57-6053 (Airbus Modification 10453).
We are superseding an existing airworthiness directive (AD) for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R airplanes. That AD currently requires performing a one-time detailed visual inspection of the forward fitting at frame (FR) 40 on both sides of the airplane for cracks, and repair if necessary. This new AD requires repetitive detailed inspections of the forward fitting at FR 40 without nut removal, and a one-time eddy current or liquid penetrant inspection of the forward fitting at FR 40 with nut removal, and repair if necessary. This AD was prompted by reports that new cracks were found in the FR 40 forward fitting. We are issuing this AD to detect and correct cracking of the FR 40 forward fitting, which could result in a deterioration of the 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 actions required by paragraphs (f)(1), (f)(2), and (f)(3) of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010).
(1) At the applicable time specified in table 1 to paragraph (g)(1) of this AD: Do a one-time detailed visual inspection of the forward fitting at FR 40 on both sides of the airplane, in accordance with Airbus Mandatory Service Bulletin A300-57A6108 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes) or A300-53A0387 (for Model A300 B4-2C, B4-103, and B4-203 airplanes), both including Appendices 01 and 02, both dated September 12, 2008.
| Airplane models/configuration | Compliance time |
|---|---|
| A300 B4-2C and B4-103 airplanes on which Airbus Service Bulletin A300-53-0297 was done prior to the accumulation of 9,000 total flight cycles | Prior to the accumulation of 18,000 total flight cycles, or within 3 months after April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)), whichever occurs later. |
| A300 B4-2C and B4-103 airplanes on which Airbus Service Bulletin A300-53-0297 was done on or after the accumulation of 9,000 total flight cycles | Within 5,500 flight cycles after accomplishment of Airbus Service Bulletin A300-53-0297, or within 6 months after April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010-06-05), have accumulated 11,000 flight cycles or more since accomplishment of Airbus Service Bulletin A300-53-0297, within 3 months after April 15, 2010 (the effective date of AD 2010-06-05). |
| A300 B4-203 airplanes on which Airbus Service Bulletin A300-53-0297 was done prior to the accumulation of 8,300 total flight cycles | Prior to the accumulation of 15,000 total flight cycles, or within 3 months after April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)), whichever occurs later. |
| A300 B4-203 airplanes on which Airbus Service Bulletin A300-53-0297 was done on or after the accumulation of 8,300 total flight cycles | Within 4,100 flight cycles after accomplishment of Airbus Service Bulletin A300-53-0297, or within 6 months after April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010-06-05), have accumulated 8,200 flight cycles or more since accomplishment of Airbus Service Bulletin A300-53-0297, within 3 months after April 15, 2010 (the effective date of AD 2010-06-05). |
| A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes on which Airbus Service Bulletin A300-57-6053 was done prior to the accumulation of 6,100 total flight cycles | Prior to the accumulation of 11,500 total flight cycles, or within 3 months after April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)), whichever occurs later. |
| A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes on which Airbus Service Bulletin A300-57-6053 was done on or after the accumulation of 6,100 total flight cycles | Within 3,300 flight cycles after accomplishment of Airbus Service Bulletin A300-57-6053, or within 6 months after April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010-06-05), have accumulated 6,600 flight cycles or more since accomplishment of Airbus Service Bulletin A300-57-6053, within 3 months after April 15, 2010 (the effective date of AD 2010-06-05). |
(2) Except as required by paragraph (g)(3) of this AD: If any crack is found during the inspection required by paragraph (g)(1) of this AD, before further flight, do a temporary or definitive repair, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7, 2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings 15R53810394, Issue A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes).
(3) If any crack found during the inspection required by paragraph (g)(1) of this AD cannot be repaired in accordance with Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7, 2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings 15R53810394, Issue A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes): Contact Airbus for repair instructions and, before further flight, repair the crack using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent).
This paragraph restates the requirements of paragraph (f)(4) of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010). Submit an inspection report in accordance with Appendix 01 of Airbus Mandatory Service Bulletin A300-53A0387, including Appendices 01 and 02, dated September 12, 2008 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or Airbus Mandatory Service Bulletin A300-57A6108, including Appendices 01 and 02, dated September 12, 2008 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes); to the address identified on the reporting sheet, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) If the inspection was done on or after April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)): Submit the report within 30 days after the inspection.
(2) If the inspection was done before April 15, 2010 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)): Submit the report within 30 days after April 15, 2010 (the effective date of AD 2010-06-05).
Within 300 flight cycles after the effective date of this AD: Perform a detailed inspection for cracks of the forward fitting at FR 40 without nut removal on both sides of the airplane, in accordance with Airbus All Operator Telex A300-53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or Airbus All Operator Telex A300-57A6111, dated August 9, 2011 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes). Thereafter, repeat the inspection at intervals not to exceed 300 flight cycles.
Within 36 months after the effective date of this AD: Perform an eddy current inspection or a liquid penetrant inspection for cracks of the forward fitting at FR 40 with nut removal on both sides of the airplane, in accordance with Airbus All Operator Telex A300-53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or Airbus All Operator Telex A300-57A6111, dated August 9, 2011 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes).
If, during any inspection required by paragraph (i) or (j) of this AD, any crack is detected: Before further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or EASA (or its delegated agent).
Submit a one-time report of the findings (both positive and negative) of the inspections required by paragraphs (i) and (j) of this AD to Airbus, Sebastien Faure, SEES1, SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 31 68; fax +33 5 61 93 36 14; email sebastien.s.faure@airbus.com, at the applicable time specified in paragraph (l)(1) or (l)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
Accomplishment of the one-time eddy current inspection or a liquid penetrant inspection required by paragraph (j) of this AD, including doing all applicable repairs, constitutes terminating action for the inspections required by paragraph (i) 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.
