2012-22-08: 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 adding the following new airworthiness directive (AD): 2012-22-08 Airbus: Amendment 39-17244; Docket No. FAA-2012-0488; Directorate Identifier 2011-NM-106-AD. (a) Effective Date This AD is effective December 20, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2- 203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category; except those airplanes identified in paragraph (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. (1) Airplanes on which Airbus Service Bulletin A300-53-6166 (Airbus Modification 13434) has been embodied in service (for Model A300 B4-600 and A300 B4-600R series airplanes). (2) Airplanes on which Airbus Service Bulletin A300-53-0389 (Airbus Modification 13434) has been embodied in service (for Model A300 series airplanes). (3) Airplanes on which Airbus Service Bulletin A310-53-2133 (Airbus Modification 13434) has been embodied in service (for Model A310 series airplanes). (4) Airplanes modified by FAA Supplemental Type Certificate (STC) ST01431NY, ST00177LA-D, or ST00100NY, as applicable. (d) Subject Air Transport Association (ATA) of America Code 53: Fuselage. (e) Reason This AD was prompted by reports of fatigue cracking in the crossbeams at the junction of the actuator beam of the lower deck cargo door. We are issuing this AD to detect and correct cracking of the crossbeams at the junction of the actuator beam of the lower deck cargo door, which could result in failure to withstand ultimate load conditions, and consequent reduced structural integrity of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Repetitive High Frequency Eddy Current Inspections (1) For airplanes on which the crossbeams at frames (FR) 22/23 and FR 61/62 have not [[Page 68052]] been repaired as specified in an Airbus structural repair manual or repair approval sheet as of the effective date of this AD: Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 600 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection for cracking of the crossbeam fuselage frame stations FR 22/23 and FR 61/62, inaccordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. Repeat the inspection thereafter at intervals not to exceed 600 flight cycles until the modification specified in paragraph (i) of this AD has been done. (i) Airbus Mandatory Service Bulletin A300-53-0390, dated January 15, 2010 (for Model A300 series airplanes). (ii) Airbus Mandatory Service Bulletin A310-53-2134, dated January 15, 2010 (for Model A310 series airplanes). (iii) Airbus Mandatory Service Bulletin A300-53-6168, dated January 15, 2010 (for Model A300-600 series airplanes). (2) For airplanes on which the crossbeams at FR 22/23 and FR 61/ 62 have been repaired as specified in an Airbus structural repair manual or repair approval sheet as of the effective date of this AD: Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 600 flight cycles after the effective date of this AD, whichever occurs later, repair in accordance with 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). (h) Corrective Action If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair any crack using a method approved by the Manager, International Branch, ANM- 116; or EASA (or its delegated agent). (i) Optional Terminating Action Modifying the crossbeam fuselage frame stations FR 22/23 and FR 61/62, including doing rotating probe inspections for cracks of fastener holes, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, and repairing any crack using a method approved by the Manager, International Branch, ANM-116; or EASA (or its delegated agent); terminates the repetitive inspections required by paragraph (g)(1) of this AD. (1) Airbus Service Bulletin A300-53-0389, Revision 02, dated April 27, 2011 (for Model A300 series airplanes). (2) Airbus Service Bulletin A310-53-2133, Revision 02, dated April 27, 2011 (for Model A310 series airplanes). (3) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 21, 2010 (for Model A300-600 series airplanes). (j) Other FAA AD Provisions 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. 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 emailed 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. (k) Related Information Refer to EASA Airworthiness Directive 2011-0086, dated May 12, 2011; and the service information identified in paragraphs (k)(1), (k)(2), (k)(3), (k)(4), (k)(5), and (k)(6) of this AD, for related information. (1) Airbus Mandatory Service Bulletin A300-53-0390, dated January 15, 2010. (2) Airbus Mandatory Service Bulletin A300-53-6168, dated January 15, 2010. (3) Airbus Mandatory Service Bulletin A310-53-2134, dated January 15, 2010. (4) Airbus Service Bulletin A300-53-0389, Revision 02, dated April 27, 2011. (5) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 21, 2010. (6) Airbus Service Bulletin A310-53-2133, Revision 02, dated April 27, 2011. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Mandatory Service Bulletin A300-53-0390, dated January 15, 2010.(ii) Airbus Mandatory Service Bulletin A300-53-6168, dated January 15, 2010. (iii) Airbus Mandatory Service Bulletin A310-53-2134, dated January 15, 2010. (iv) Airbus Service Bulletin A300-53-0389, Revision 02, dated April 27, 2011. (v) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 21, 2010. (vi) Airbus Service Bulletin A310-53-2133, Revision 02, dated April 27, 2011. (3) 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; email [email protected]; Internet http://www.airbus.com. (4) You may review copies of the referenced 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. (5) You may view this 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/cfr/ibr-locations.html.