2009-18-16 Airbus: Amendment 39-16012. Docket No. FAA-2009-0465; Directorate Identifier 2007-NM-244-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October 14, 2009.
Affected ADs
(b) This AD supersedes AD 2006-02-06, Amendment 39-14458.
Applicability
(c) This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324 and -325 airplanes; all serial numbers; certificated in any category; except those airplanes on which Airbus Mandatory Service Bulletin A310-53-2124, dated April 4, 2005, has been accomplished.
Subject
(d) Air Transport Association (ATA) of America Code 53: Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD F-2005-078 [which corresponds to FAA AD 2006-02-06, Amendment 39-14458, 71 FR 3214, January 20, 2006] to require the modification (Airbus modification 13023), defined in Airbus SB [service bulletin] A310-53-2124, to increase the service life of junctions of center box upper frame bases to upper fuselage arches. This structural modification falls within the scope of the work related to the extension of the service life of A310 aircraft and widespread fatigue damage evaluations.
The threshold timescales for accomplishment of the tasks as defined in SB A310-53-2124 were refined and reduced. Consequently, EASA issued AD 2007-0238 to require compliance with Revision 1 of SB A310-53-2124 at the reduced compliance times, superseding (the requirements of) DGAC France AD F-2005-078. Subsequently, Airbus identified reference material that was erroneously introduced into Airbus SB A310-53-2124 Revision 1. As a result, the SB instructions could not be accomplished properly. Operators that tried to apply SB A310-53-2124 at Revision 1 had to contact Airbus; see also Airbus SBIT [service bulletin information telex] ref. 914.0135/08, dated 03 March 2008.
Consequently, AD 2007-0238 was revised to exclude reference to Airbus SB A310-53-2124 Revision 1 and to require accomplishment of the task(s) as described in the original SB A310-53-2124 instead, although retaining the reduced compliance times introduced by AD 2007-0238 at original issue. This new [EASA] AD is published to refer to Airbus SB A310-53-2124 Revision 02, the corrected version that is to be used to meet the requirements of this AD.
The unsafe condition is fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and which could result in reduced structural integrity of the fuselage. The required actions include inspecting by rotating probe for cracking of holes H1 through H29 on frame (FR) 43 through 46 inclusive, and inspecting holes H1 through H29 on FR 43 through 46 inclusive to determine the edge distance of the hole, and corrective actions if necessary.
Requirements of This AD: Actions and Compliance
(f) Unless already done, do the following actions.
(1) Except for airplanes identified in paragraph (f)(2) of this AD, at the later of the times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, accomplish inspections by rotating probe for cracking of holes H1 through H29 on frame FR 43 through 46 inclusive, and inspections of holes H1 through H29 on FR 43 through 46 inclusive to determine the edge distance of the hole, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008 ("the service bulletin''). If no cracking is found and the edge distance is equal to or greater than the distance specified in the Accomplishment Instructions of the service bulletin, before further flight, do the cold expansion of the most fatigue sensitive fastener holes, as identified in the service bulletin.
(i) Inspect at the applicable time indicated in Table 1 of this AD. Airbus Model A310-304, -322,-324, and -325 airplanes with an average flight time (AFT) equal to or less than 3.17 flight hours are short range airplanes. Airbus Model A310-304, -322, -324, and - 325 airplanes with an AFT exceeding 3.17 flight hours are long range airplanes.
(ii) Within 500 flight cycles or 800 flight hours after the effective date of this AD, whichever occurs first.
Table 1--Compliance Times
Affected Airplanes
Inspection/Modification Threshold, whichever occurs later
Model A310-304, -322, -324 and
-325 short range airplanes
Prior to accumulation of 26,500 flight cycles or 74,300 flight hours since first flight of the airplane, whichever occurs first
Within 3,000 flight cycles after the effective date of this AD, without exceeding 29,200 flight cycles or 81,800 flight hours since first flight, whichever occurs first
Model A310-304, -322, -324 and
-325 long range airplanes
Prior to accumulation of 23,400 flight cycles or 117,100 flight hours since first flight of the airplane, whichever occurs first
Within 3,000 flight cycles after the effective date of this AD, without exceeding 25,800 flight cycles or 129,000 flight hours since first flight, whichever occurs first
Model A310-203, -204, -221, and A310-222
Prior to accumulation of 23,400 flight cycles or 46,800 flight hours since first flight of the airplane, whichever occurs first
Within 3,000 flight cycles after the effective date of this AD, without exceeding 28,800 flight cycles or 57,700 flight hours since first flight, whichever occurs first
Note 1: To establish the average flight time, take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the average flight time per flight cycle.
(2) For airplanes that have been modified before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A310-53-2124, Revision 01, dated May 3, 2007: Within 500 flight cycles or 800 flight hours after the effective date of this AD, whichever occurs first, contact Airbus and follow their corrective actions.
(3) If, during any inspection required by paragraph (f)(1) of this AD, any cracking is found or if the edge distance is less than the distance specified in Airbus Mandatory Service Bulletin A310-53- 2124, Revision 02, dated May 22, 2008, before further flight, contact Airbus and follow their corrective actions.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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 98055-4056; 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. 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.
(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 European Union Airworthiness Directive 2008- 0212, dated December 4, 2008; and Airbus Mandatory Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008; for related information.
Material Incorporated by Reference
(i) You must use Airbus Mandatory Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008, to do the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008, under 5 U.S.C. 552 (a) and 1 CF 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: account.airworth-eas@airbus.com; 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 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.