2011-17-05: Fuselage

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Amendment 39-6448 (55 FR 261, January 4, 1990) and adding the following new AD: 2011-17-05 Airbus: Amendment 39-16769. Docket No. FAA-2011-0389; Directorate Identifier 2007-NM-189-AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 16, 2011. Affected ADs (b) This AD supersedes AD 90-01-10, Amendment 39-6448 (55 FR 261, January 4, 1990). Applicability (c) This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; certificated in any category; serial numbers 0003 through 0156 inclusive. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: This Airworthiness Directive (AD) is issued in order to prevent cracks development in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames 18 and 80 which could affect the structural integrity of the fuselage if not corrected. This new AD: --Retains the requirements of DGAC AD 1989-061-092(B)R4 [which corresponds to FAA AD 90-10-10 (55 FR 261, January 4, 1990)], which is cancelled; --Takes into account a new inspection program as detailed in AIRBUS Service Bulletins (SB) A300-53-0211 Revision 7, which will allow A300 aircraft to reach the Limit of Validity (LOV). This AD has been republished to correctly refer to SB A300-53- 0211 in Note 2 of the Compliance section. The inspection program consists of repetitive detailed inspections for disbonding and cracking of the fuselage inner doubler; eddy current and ultrasonic inspections of the fuselage longitudinal lap joints for cracking; and repair if necessary (i.e., repairing any cracking or disbonding, or contacting Airbus for repair instructions and doing the repair). Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections of ``Special Areas'' and Repair or Modification if Necessary (g) For airplanes on which an eddy current inspection of the ``special'' areas of the longitudinal lap joints has not been done as of the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300-53-0211: Prior to the accumulation of 24,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later; do an eddy current inspection for cracking of the ``special'' areas of the longitudinal lap joints, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 1 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ``Special'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. [[Page 63179]] Table 1--Repetitive Intervals for Inspecting Special Areas of the Longitudinal Lap Joints ---------------------------------------------------------------------------------------------------------------- Inspect special area-- For airplanes-- Repeat at intervals not to exceed-- ---------------------------------------------------------------------------------------------------------------- All................................. STGR5 LH and RH (FR54 3,600 flight cycles. through FR58). All................................. STGR22 LH and RH 2,700 flight cycles. (FR26 through FR40). All................................. STGR22 RH (FR58 3,000 flight cycles. through FR65). All................................. STGR31 LH/RH (FR26 3,000 flight cycles. through FR39). MSN 0003............................ STGR31 LH/RH (FR54 3,600 flight cycles. through FR58). ---------------------------------------------------------------------------------------------------------------- (h) For airplanes on which an eddy current inspection of the ``special'' areas of the longitudinal lap joints has been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211; except for airplanes on which a repair or modification of the ``special'' areas has been done in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: Do the next inspection of the ``special'' areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 2 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07,dated December 1, 2006, and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ``Special'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. (1) Within 6,000 flight cycles after doing the last inspection of the ``special'' areas of the longitudinal lap joints, in accordance with Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. (2) Within the applicable intervals specified in Table 2 of this AD, or within 60 days after the effective date of this AD, whichever occurs later. Table 2--Repetitive Intervals for Inspecting Special Areas of the Longitudinal Lap Joints ---------------------------------------------------------------------------------------------------------------- Inspect special area-- For airplanes-- Repeat at intervals not to exceed-- ---------------------------------------------------------------------------------------------------------------- All................................. STGR5 LH and RH (FR54 3,600 flight cycles. through FR58). All................................. STGR22 LH and RH 2,700 flight cycles. (FR26 through FR40). All................................. STGR22 RH (FR58 3,000 flight cycles. through FR65). All................................. STGR31 LH/RH (FR26 3,000 flight cycles. through FR39). MSN 0003............................ STGR31 LH/RH (FR54 3,600 flight cycles. through FR58). ---------------------------------------------------------------------------------------------------------------- Repetitive Inspections of ``Standard Areas'' and Repair or Modification if Necessary (i) For airplanes on which an eddy current inspection of the ``standard'' areas of the longitudinal lap joints has not been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: At the applicable time specified in Tables 3 and 4 of this AD, do an eddy current inspection for cracking of the longitudinal lap joints in the ``standard'' areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Repeat the inspection thereafter at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the applicable area specified in Tables 3 and 4 of this AD. ``Standard'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Table 3--Initial Compliance Times and Repetitive Intervals for Inspecting Standard Areas of the Longitudinal Lap Joints ---------------------------------------------------------------------------------------------------------------- Before the For airplanes-- accumulation Inspect Repeat at intervals not to exceed-- of-- standard area-- ---------------------------------------------------------------------------------------------------------------- All........................... 32,000 total STGR5, 13, 22 3,600 flight cycles. flight cycles. LH and RH, STGR31 LH (FR18 through FR26). All........................... 32,000 total STGR27 RH, 8,000 flight cycles. flight cycles. STGR39 RH (FR18 through FR20A, FR25A, FR26). All........................... 32,000 total STGR43 LH, 5,700 flight cycles. flight cycles. STGR46 RH, STGR51 LH (FR19 through FR26). All...........................32,000 total STGR5 LH/RH 3,000 flight cycles. flight cycles. (FR26 through FR40); STGR11 LH/RH (FR27 through FR32); STGR13 LH/RH (FR 26 through FR28, FR31 through FR40); STGR27 LH/RH (FR 27 through FR32); STGR43 LH/RH (FR 26 through FR39); STGR49 RH (FR26 through FR39). All........................... 32,000 total STGR47 LH (FR26 5,700 flight cycles. flight cycles. through FR39). All........................... 32,000 total STGR5, 13, 22 5,000 flight cycles. flight cycles. LH/RH (FR40 through FR54). [[Page 63180]] All except MSN 0003........... 32,000 total STGR13, 44, 52 3,600 flight cycles. flight cycles. LH/RH (FR54 through FR58); STGR22 LH/RH (FR54, FR55); STGR31 LH/RH (FR54 through FR58). ---------------------------------------------------------------------------------------------------------------- (j) For airplanes on which an eddy current inspection of the ``standard'' areas of the longitudinal lap joints has been done as of the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211; except for airplanes on which a repair or modification of the ``standard areas'' has been done in accordance with Airbus Mandatory Service Bulletin A300-53-0211: Do the next inspection of the ``standard'' areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Thereafter, if no cracking is found, repeat the inspection at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ``Standard'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Table 4--Initial Compliance Times and Repetitive Intervals for Inspecting Additional Standard Areas of the Longitudinal Lap Joints ---------------------------------------------------------------------------------------------------------------- Before the For airplanes-- accumulation Inspect Repeat at intervals not to exceed-- of-- standard area-- ---------------------------------------------------------------------------------------------------------------- Pre-Mod 1398.................. 32,000 total STGR5, 13 LH/RH 2,700 flight cycles. flight cycles. 22 LH (FR58 through FR65); STGR31 LH (FR58 throughFR72); STGR31 RH (FR65 through FR72). All........................... 32,000 total STGR27 RH, 8,000 flight cycles. flight cycles. STGR39 RH (FR58, FR59A, FR63A through FR65). Post-Mod 1398................. 32,000 total STGR5, 13 LH/RH 3,000 flight cycles. flight cycles. 22 LH (FR58 through FR65); STGR31 LH (FR58 through FR72); STGR 31 RH (FR65 through FR72). Pre-Mod 1398.................. 32,000 total STGR5, 13, 22 2,300 flight cycles. flight cycles. LH/RH (FR65 through FR72). Post-Mod 1398................. 32,000 total STGR5, 13, 22 3,000 flight cycles. flight cycles. LH/RH (FR65 through FR72). All........................... 32,000 total STGR44 LH (FR58 3,000 flight cycles. flight cycles. through FR72); STGR52 LH/RH (FR58 through FR65); STGR47 RH (FR58 through FR72); STGR57 LH (FR65 through FR72). All........................... 24,000 total STGR22 RH (FR583,000 flight cycles. flight cycles. through FR65). All........................... 32,000 total STGR6 LH/RH 3,000 flight cycles. flight cycles. (FR72 through FR80); STGR24 LH/RH (FR76 through FR80). All........................... 32,000 total STRG17 LH/RH 5,700 flight cycles. flight cycles. (FR76 through FR80); STGR29 LH/RH (FR72 through FR76); STGR35 LH/RH (FR72 through FR80). All........................... 27,000 total STGR51 LH/RH 5,700 flight cycles. flight cycles. (FR72 through FR80). ---------------------------------------------------------------------------------------------------------------- (1) Within the applicable time in paragraph (j)(1)(i) or (j)(1)(ii) of this AD after doing the last inspection of the ``standard'' areas of the longitudinal lap joints in accordance with Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. (i) For longitudinal lap jointswith bonded doublers: 6,000 flight cycles. (ii) For longitudinal lap joints without bonded doublers: 8,000 flight cycles. (2) Within the applicable time specified in Tables 3 or 4 of this AD, or within 60 days after the effective date of this AD, whichever occurs later. Post-Repair or Modification Inspections and Repair or Modification if Necessary (k) For airplanes on which a repair or modification has been done in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: At the applicable initial inspection time specified in Table 5 of this AD, do an eddy current inspection for cracking of the repaired or modified areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 5 of this AD. If any crack is found during any inspection requiredby this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. [[Page 63181]] Table 5--Post-Repair or Modification Compliance Time ---------------------------------------------------------------------------------------------------------------- Repair or retrofit solution/area-- as identified in Airbus Mandatory Initial inspection after Follow-up inspections at intervals not to exceed-- Service Bulletin A300-53-0211-- repair or retrofit-- ---------------------------------------------------------------------------------------------------------------- Repair 1: (Without cut out) also Skin/doubler thickness applicable to the solution with removed inner doubler. < 1 inch: 10,000 1,000 flight cycles. flight cycles after repair. >= 1 inch and < 2,000 flight cycles. 2 inch: 30,000 flight cycles after repair. >= 2 inch: 6,400 flight cycles. 60,000 flight cycles after repair. Repair 4 (With cut out).......... Within 32,000 flight 5,000 flight cycles. cycles after repair. Repair 4A (With cut out)......... Within 24,000 flight 5,300 flight cycles. cycles after repair. Repair 7 (MSN 0095 at STGR52 LH Within 37,000 flight 12,000 flight cycles. in Section 16). cycles after repair. Repair 9 (MSN 0073 and 0095 Within 36,000 flight 5,000 flight cycles. STGR44 LH/RH in Sections 16 and cycles after repair. 17). Repair 10 (Post-repair Within 20,000 flight 11,000 flight cycles. inspections in Figure 13). cycles after repair. Repair 2 (With cut out).......... Within 24,000 flight 5,300 flight cycles. cycles after repair. Repair 3 (Without cut out)....... Within 24,000 flight 5,300 flight cycles. cycles after repair. Retrofit 1 (Retrofit lap joint).. Within32,000 flight 5,000 flight cycles. cycles after retrofit. Retrofit 2 Retrofit lower shell Within 32,000 flight 3,000 flight cycles. (4 panel solution) STGR43 LH cycles after retrofit. (FR26 through FR39), STGR43 RH (FR26 through FR38), and STGR49 RH (FR26 through FR38). Retrofit 2 Retrofit lower shell Within 32,000 flight 5,700 flight cycles. (4 panel solution) STGR46 RH cycles after retrofit. (FR19 through FR26), and STGR47 LH (FR26 through FR39), and STGR51 LH (FR19 through FR26). Retrofit 3 Retrofit lower shell Within 32,000 flight 3,000 flight cycles. (3 panel solution) STGR43 LH cycles after retrofit. (FR26 through FR39), and STGR43 RH (FR26 through FR38). Retrofit 3 Retrofit lower shell Within 32,000 flight 5,700 flight cycles. (3 panel solution) STGR46 RH cycles after retrofit. (FR19 through FR26), and STGR51 LH (FR19 through FR26), and STGR54 LH (FR26 through FR39).Retrofit 3A (STGR43 LH/RH between Within 32,000 flight 5,000 flight cycles. FR37 and FR39 in Section 14). cycles after retrofit. Retrofit 4 (Retrofit lap joint Within 42,000 flight 5,000 flight cycles. without cut out). cycles after retrofit. Retrofit 5 (Retrofit lap joint).. Within 42,000 flight 5,000 flight cycles. cycles after retrofit. Retrofit 6 (Retrofit lap joint).. Within 34,000 flight 12,000 flight cycles. cycles after retrofit. Retrofit 7 (Retrofit lap joint).. Within 47,600 flight 5,400 flight cycles. cycles after retrofit. ---------------------------------------------------------------------------------------------------------------- Fuselage Inner Doubler Inspections and Repair if Necessary (l) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have not been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 15 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 6 of this AD. Table 6--Repetitive Intervals for Inspections for Disbonding and Cracking ------------------------------------------------------------------------ Inspect at intervals not toexceed-- For area-- ------------------------------------------------------------------------ Sections 13 and 14 as specified in Within 7 years or 12,000 flight Airbus Service Bulletin cycles after doing the inspection, A300[dash]53[dash]229, Revision 5, whichever occurs first. dated April 8, 1997. Sections 15 through 18 as specified Within 8.5 years or 12,000 flight in Airbus Service Bulletin cycles after doing the inspection, A300[dash]53[dash]229, Revision 5, whichever occurs first. dated April 8, 1997. ------------------------------------------------------------------------ (1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (m) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229; except for airplanes on which a repair of that area has been done in accordance with Airbus Service [[Page 63182]] Bulletin A300-53-229: At the applicable time specified in Table 6 of thisAD, or within 60 days after the effective date of this AD, whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection at the applicable intervals specified in Table 6 of this AD. (1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5,dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (n) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have not been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 12 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (o) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229; except airplanes on which a repair of that area has been done in accordance with Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and corrosion are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found and ``major'' disbonding, as defined inAirbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (p) Although Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997; and Airbus Mandatory Service Bulletin A300-53- 0211, Revision 07, dated December 1, 2006; specify to submit certain information to the manufacturer, this AD does not include that requirement. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: (1) Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, this AD requires that you repair the crack(s) before further flight. (2) The MCAI or service information does not include enforceable compliance times for certain actions; however, this AD requires that those actions be done at the enforceable times specified in this AD. (3) Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (p) of this AD specifies that such submittal is not required. Other FAA AD Provisions (q) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Information may be e-mailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Related Information (r) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007-0091, dated April 10, 2007, corrected June 23, 2008; Airbus Service BulletinA300-53-229, Revision 5, dated April 8, 1997; and Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; for related information. Material Incorporated by Reference (s) You must use Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, including Appendix A300SB/53-229, dated April 10, 1989; and Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. Only pages 1, 2, 5, 11, and 12, of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, show revision level 5 and issue date April 8, 1997; pages 3, 4-10, and 13-17 show revision level 4 and issue date March 30, 1994, and pages 1-17 of Appendix A300SB/53- 229 show issue date April 10, 1989. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) Forservice information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; [[Page 63183]] telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail [email protected]; Internet http://www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.