AD 2005-12-07 Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes

Models named: A319, A320, A321 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A319, A320, and A321 series airplanes, certificated in any category; except those on which Airbus Modification 32025 was done during production.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. One-Time Ultrasonic Inspection/Repair (f) For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: At the earliest of the times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD; perform a one-time ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320-57A1136, dated January 26, 2005. Repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). (1) Within 750 flight cycles after the effective date of this AD. (2) Within 600 flight hours after the effective date of this AD. (3) Within 100 days after the effective date of this AD. Repetitive Detailed Inspections (g) Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG at the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, and repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent). Accomplishing the actions specified in the Airbus A318/A319/A320/A321 Non-destructive Testing Manual, Chapter 51-90-00, revision dated February 2003, is one approved method for performing the detailed inspection. Repeat the inspection thereafter at intervals not to exceed 750 flight cycles, 600 flight hours, or 100 days, whichever occurs earliest. (1) For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: Do the detailed inspection within 100 days after the effective date of this AD or at the earliest of the times specified in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD, whichever is later. (i) Within 750 flight cycles after accomplishing the ultrasonic inspection. (ii) Within 600 flight hours after accomplishing the ultrasonic inspection. (iii) Within 100 days after accomplishing the ultrasonic inspection. (2) For all other airplanes: Do the detailed inspection at the earliest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Within 750 flight cycles after the effective date of this AD. (ii) Within 600 flight hours after the effective date of this AD. (iii) Within 100 days after the effective date of this AD. 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.” Optional Terminating Action (h) Modification of the lugs of the support rib 5 fitting of the left- and right-hand MLG and accomplishment of all related investigative actions and all applicable corrective actions in accordance with Airbus Service Bulletin A320-57-1118, dated September 5, 2002; or Revision 01, dated August 28, 2003; constitutes compliance with the requirements of this AD. (i) Repair of the forward lugs of the support rib 5 fitting of the left- and right-hand MLG in accordance with Airbus A319 Structural Repair Manual, Chapter 5.C., 57-26-13: Airbus A320 Structural Repair Manual, Chapter 5.D., 57-26-13; and Airbus A321 Structural Repair Manual, Chapter 5.D., all revisions dated November 1, 2004, constitutes compliance with the requirements of this AD. Alternative Methods of Compliance (AMOCs) (j) 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. Related Information (k) French airworthiness directive F-2005-035, dated March 2, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A320-57A1136, dated January 26, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC. To review copies of the service information, go to 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. Issued in Renton, Washington, on June 6, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-11707 Filed 6-14-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by a report of a crack found in the forward lug of the right-hand main landing gear (MLG) rib 5 fitting during greasing of the MLG pintle bearings. The FAA is issuing this AD to find and fix cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during landing.