Airworthiness directives › 2006-11-04
AD 2006-11-04 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes
Models named: A318, A319, A320, A321. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category; except those on which Airbus Modification 32025 was done during production.
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. Repetitive Detailed Inspections (f) Within 8 days after the effective date of this AD, or before further flight after a hard landing, whichever is first: Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG, and, if any crack is found, replace the MLG fitting with a new fitting before further flight, in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Accomplishing the actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 51-90-00, revision dated February 1, 2003, is one approved method for performing the detailed inspection. Repeat the inspection thereafter at intervals not to exceed 8 days, or before further flight after a hard landing, whichever is first. 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 Inspection Method (g) Performing an ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent), is an acceptable alternative method of compliance for the initial and repeat inspections required by paragraph (f) of this AD. Doing the actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 57-29-03, revision dated February 1, 2005 (for Airbus Model A318, A319, and A320 airplanes), or Chapter 57-29-04, revision dated May 1, 2005 (for Airbus Model A321 airplanes), as applicable, is one approved method for performing the ultrasonic inspection. Optional Terminating Action (h) For Model A319, A320, and A321 airplanes; as identified in Airbus Service Bulletin A320-57-1118, dated September 5, 2002; or Revision 01, dated August 28, 2003: Modifying the lugs of the support rib 5 fitting of the left- and right-hand MLG and accomplishing all related investigative actions and all applicable corrective actions in accordance with Airbus Service Bulletin A320-57-1118, or Revision 01, constitutes terminating action for the requirements of this AD. (i) For Model A319, A320, and A321 airplanes: Repair of the forward lugs of the support rib 5 fitting of the left- and right-hand MLG in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent), constitutes terminating action for the requirements of this AD. Doing the repair in accordance with Airbus A319 Structural Repair Manual Chapter 5.C., 57-26-13, or Airbus A320 Structural Repair Manual Chapter 5.D., 57-26-13; revisions dated November 1, 2004; or Airbus A321 Structural Repair Manual, Chapter 5.D., 57-26-13, revision dated February 1, 2005; as applicable; is one approved method. Alternative Methods of Compliance (AMOCs) (j)(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 § 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 (k) EASA emergency airworthiness directive 2006-0069R1, dated April 7, 2006, also addresses the subject of this AD. Material Incorporated by Reference (l) None. Issued in Renton, Washington, on May 15, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-4712 Filed 5-22-06; 8:45 am] BILLING CODE 4910-13-P
Unsafe condition
This AD results from a new crack that was found in the forward lug of the MLG support rib 5 fitting. We are issuing this AD to detect and correct cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during takeoff or landing.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1