2005-23-21: Thrust reverser forward frame

2005-23-21 Airbus: Amendment 39-14379. Docket No. FAA-2005-23005; Directorate Identifier 2003-NM-110-AD. Effective Date (a) This AD becomes effective December 6, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A340-211, -212, and -213 and A340-311, -312, and -313 airplanes, certificated in any category. Unsafe Condition (d) This AD results from fatigue and damage tolerance testing of the engine thrust reversers which revealed fatigue cracking of the junction between the thrust reverser forward frame and the 12 o'clock beam, and of the thrust reverser J-ring structure. We are issuing this AD to detect and correct such fatigue cracking, which could result in rupture of the J-ring, forward frame, or common fittings; loss of the thrust reverser system; or inadvertent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane. Compliance (e) You are responsible for havingthe actions required by this AD performed within the compliance times specified, unless the actions have already been done. Note 1: For the purposes of this AD, a detailed inspection is: "An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required." Repetitive Inspections/Investigative and Corrective Actions (f) Accomplish detailed and eddy current inspections for cracking of the junction between the thrust reverser forward frame and the 12 o'clock and 6 o'clock beams, and the thrust reverser common fittings, and related investigative and corrective actions, by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-78-4028, Revision 01, dated October 23, 2003. Except, if damage is found on the common fittings, repair the damage using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Do the inspections at the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD. Do any related investigative and corrective actions before further flight in accordance with the service bulletin. Repeat the inspections thereafter at intervals not to exceed 4,500 flight cycles on the thrust reverser. (1) For thrust reversers that have accumulated fewer than 4,500 total flight cycles since new as of the effective date of this AD: Before the accumulation of 4,500 total flight cycles on the thrust reverser since new, or within 2,166 flight cycles after the effective date of this AD, whichever is later. (2) For thrust reversers that have accumulated 4,500 or more total flight cycles since new as of the effective date of this AD: Before the accumulation of 6,666 total flight cycles on the thrust reverser since new or within 6 months after the effective date of this AD, whichever is later. Note 2: Airbus Service Bulletin A340-78-4028, Revision 01, dated October 23, 2003, references Rohr Service Bulletin RA34078-71, Revision 1, dated February 7, 2003, as an additional source of service information for accomplishing the applicable actions in paragraph (f) of this AD. (g) At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Accomplish an eddy current inspection for cracking of the J-ring structure at the 12 o'clock and 6 o'clock positions by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 27, 2004. If no cracking is found: Repeat the inspection thereafter at intervals not to exceed 800 flight hours or 175 flight cycles on thethrust reverser, whichever is first. (1) Before the accumulation of 3,000 total flight cycles on any thrust reverser since new. (2) Within 800 flight hours or 175 flight cycles after the effective date of this AD, whichever is first. (h) If any cracking is found at the 12 o'clock position, before further flight, do the actions required by either paragraph (h)(1) or (h)(2) of this AD. (1) Replace the thrust reverser by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 27, 2004. (2) Modify the J-ring and replace the 12 o'clock fitting by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0073, Revision 1, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-73, Revision 1, dated January 27, 2004. Except, if any crackingis found on machined parts, repair the damage using a method approved by the Manager, International Branch, ANM-116. Repeat the inspection of the 6 o'clock position only at the time specified in paragraph (g) of this AD. (i) If cracking is found at the 6 o'clock position: Before further flight, replace the thrust reverser by doing all the applicable actions in accordance with CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 27, 2004. No Reporting Required (j) Although Airbus Service Bulletin A340-78-4028, Revision 01, dated October 23, 2003; and CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, specify reporting the replacement of any thrust reverser to Airbus or CFM, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with Sec. 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (l) French airworthiness directives 2003-108(B), dated March 19, 2003; and F-2004-020, dated February 4, 2004, also address the subject of this AD. Material Incorporated by Reference (m) You must use Airbus Service Bulletin A340-78-4028, Revision 01, excluding Appendix 01, dated October 23, 2003; CFM International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 27, 2004; and CFM International CFM56-5C Alert Service Bulletin 78-A0073, Revision 1, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78-73, Revision 1, dated January 27, 2004; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; or Rohr Inc., 850 Lagoon Drive, Chula Vista, California 91912, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .