2009-20-06: Fuselage

2009-20-06 Airbus: Amendment 39-16029. Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-174-AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 3, 2009. Affected ADs (b) This AD supersedes AD 88-06-03, Amendment 39-5871. Applicability (c) This AD applies to Airbus Model A310-203 and -222 airplanes, and Model A300 B4-620 airplanes; certificated in any category; all serial numbers except airplanes on which Airbus Modification 05526 has been incorporated in production. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: DGAC (Direction Generale de l'Aviation Civile) France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03, amendment 39-5871] was issued to prevent development of damage, which was discovered during [a] fatigue test in the attachment angles of the rear pressure bulkhead (fuselage frame 80/82). Following the life extension activities linked to the A310 program, the interval of inspection for A310-200 aircraft series was reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the issuance of EASA AD 2007-0157, superseding DGAC France AD 86-102- 74(B). Some stress analysis conducted in the frame of the life extension activities of the A300-600 program leads the manufacturer to reduce as well the interval of inspection applicable to A300B4- 620 and A300C4-620 aircraft models. EASA AD 2007-0297 superseded EASA AD 2007-0157, retaining for A310 aircraft the requirements of EASA AD 2007-0157 and requiring the application of Airbus Service Bulletin (SB) A300-53-6005 Revision 4 on Airbus A300-600 aircraft, reducing the inspection interval from 12000 FC to 9000 FC. [EASA] AD [2007-0297] has been revised to remove an inappropriate reference regarding the normal inspection program from the Compliance section, Note 3. The unsafe condition is cracking inthe attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. The required actions include a modification of the rear pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82; applicable related investigative and corrective actions; and, for certain airplanes, repetitive inspections for cracks in the rear pressure bulkhead and repair if necessary. Requirements of This AD: Actions and Compliance (f) Unless already done, do the following actions. Modification (1) Except as required by paragraph (f)(2) of this AD: Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later, modify the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame 80/82 and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus Mandatory Service Bulletin A310-53-2025, Revision 06, dated August 3, 2006; as applicable. Do all applicable related investigative and corrective actions before further flight. (2) For airplanes identified in paragraph (c) of AD 2006-22-03, amendment 39-14800: At the earlier of the compliance times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions specified in paragraph (f)(1) of this AD. (i) Before the accumulation of 12,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (ii) At the compliance time specified in paragraph (h) of AD 2006-22-03. Inspections and Corrective Action (3) For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done after the accumulation of 6,000 total flight cycles since first flight: At the times specifiedin paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an eddy current inspection for any cracking in the critical area of the rear pressure bulkhead between stringers 8 and 18, and repair all cracking before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-6005, Revision 04, dated July 18, 2007; or Airbus Mandatory Service Bulletin A310-53-2024, Revision 05, dated October 13, 2006; as applicable. (i) Before or concurrently with the modification required by paragraph (f)(1) or (f)(2) of this AD, as applicable; and (ii) Before the accumulation of 18,000 total flight cycles since first flight, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 9,000 flight cycles. Note 1: For airplanes on which the modification required by paragraph (f)(1) or (f)(2) of this AD is done at or before the accumulation of 6,000 total flight cycles sincefirst flight: No action is required by this AD. For these airplanes, refer to Airbus A300-600 ALI Task 531919-01-1A or Airbus A310 ALI Task 531919-01-1A, as applicable, for guidance on the normal inspection program. (4) Modifications done before the effective date of this AD in accordance with the service bulletins identified in Table 1 of this AD are acceptable for compliance with the requirements of paragraph (f)(1) and (f)(2) of this AD. Table 1--Modifications Done Using Previous Service Bulletins Model Airbus Service Bulletin Revision Dated A300-53-6006 Original May 6, 1986 A300-53-6006 1 September 19, 1986 A300 B4-620 airplanes A300-53-6006 2 August 11, 1988 A310-53-2025 Original April 21, 1986 A310-53-2025 1 September 19, 1986 A310-53-2025 2 February 16, 1987 A310-53-2025 3 April 7, 1987 A310-53-2025 4 October 20, 1987 A310-203 and -222 airplanes A310-53-2025 5 March 24, 1989 (5) Inspections done before the effective date of this AD in accordance with the service bulletins identified in Table 2 of this AD are acceptable for compliance with the requirements of paragraph (f)(3) of this AD. Table 2--Inspections Done With Previous Service Bulletins Model Airbus Service Bulletin Revision Dated A300 B4-620 airplanes A300-53-6005 Original May 6, 1986 A300-53-6005 1 June 20, 1986 A300-53-6005 2 September 22, 1986 A300-53-6005 3 April 22, 1987 A310-203 and -222 airplanes A310-53-2024 Original April 21, 1986 A310-53-2024 1 June 20, 1986 A310-53-2024 2 October 2, 1986 A310-53-2024 3 February 17, 1987 A310-53-2024 4 February 2, 1988 (6) Modification of the aft pressure bulkhead to improve the fatigue life of the attachment angles at frame (FR) 80/82 in accordance with paragraph (h) of AD 2006-22-03 is acceptable for compliance with the corresponding requirement of paragraphs (f)(1) and (f)(2) of this AD. FAA AD DifferencesNote 2: This AD differs from the MCAI and/or service information as follows. This AD includes a compliance time specified in paragraph (f)(2) of this AD for airplanes that are also affected by AD 2006-22-03. We realize that the requirements of this AD will necessitate that some operators do the modification required by paragraph (h) of AD 2006-22-03 early. However, accomplishing the modification within the compliance time specified in this AD is required to address cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Stafford, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120- 0056. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007-0297R1, dated September 17, 2008, and the service bulletins listed in Table 3 of this AD, for related information. Table 3--Related Service Bulletins Airbus Service Bulletin Revision Date Airbus Mandatory Service Bulletin A300-53-6005 04 July 18, 2007 Airbus Mandatory Service Bulletin A310-53-2024 05 October 13, 2006 Airbus Mandatory Service Bulletin A310-53-2025 06 August 3, 2006 Airbus Service Bulletin A300-53-6006 3 March 24, 1989 Material Incorporated by Reference (i) You must use the service information contained in Table 4 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 4--Material Incorporated by Reference Airbus Service Bulletin Revision Date Airbus Mandatory Service Bulletin A300-53-6005 04 July 18, 2007 Airbus Mandatory Service Bulletin A310-53-2024 05 October 13, 2006 Airbus Mandatory Service Bulletin A310-53-2025 06 August 3, 2006 Airbus Service Bulletin A300-53-6006 3 March 24, 1989 Airbus Service Bulletin A300-53-6006, Revision 3, dated March 24, 1989, contains the following effective pages: Page Number Revision level shown on page Date shown on page 1, 29, 47, 48. 3 March 24, 1989 2-28, 30-46, 49-52 2 August 11, 1988 (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) For service information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; 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. Forinformation on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (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.