Airworthiness Directive · Amendment 39-15283 · Airbus Model A310 Series Airplanes
Airbus Model A310 Series Airplanes
Superseded. A later AD replaced this one: AD 2011-10-17. Comply with the one in force.
This AD applies to all Airbus Model A310 series airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25.1529-1.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new and revised structural inspections and inspection intervals. This AD results from issuance of new and revised structural inspections and inspection intervals. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 3 months after the effective date of this AD, do the actions specified in paragraphs (f)(1) and (f)(2) of this AD.
(1) Revise the ALS of the ICA to incorporate the structural inspections and inspection intervals defined in Airbus A310 Airworthiness Limitations Items (ALI) Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006 (approved by the European Aviation Safety Agency (EASA) on May 31, 2006) (hereafter referred to as “Issue 6 of the ALI”). Accomplish the actions specified in Issue 6 of the ALI at the times specified in that ALI, except as provided by paragraph (g) of this AD. Thereafter, except as provided by paragraphs (f)(2) and (j) of this AD, no alternative structural inspection intervals may be approved. The actions specified in Issue 6 of the ALI must be accomplished in accordance with Issue 6 of the ALI.
(2) Revise the ALS of the ICA to incorporate the new and revised structural inspections and inspection intervals defined in Airbus Temporary Revision (TR) 6.1, dated November 2006 (approved by the EASA on December 12, 2006), to Issue 6 of the ALI. Thereafter, except as provided by paragraph (j) of this AD, no alternative structural inspection intervals may be approved.
The tolerance (grace period) for compliance with Issue 6 of the ALI is within 1,500 flight cycles after the effective date of this AD provided that none of the following is exceeded:
(1) Thresholds or intervals in the operator's current approved maintenance schedule that are taken from a previous ALI issue, if existing, and are higher than or equal to those given in Issue 6 of the ALI.
(2) 18 months after the effective date of this AD.
(3) 50 percent of the intervals given in Issue 6 of the ALI.
(4) Any application tolerance specified in Section D of Issue 6 of the ALI.
Damaged, cracked, or corroded structure detected during any inspection done in accordance with Issue 6 of the ALI must be repaired, before further flight, in accordance with Issue 6 of the ALI; or in accordance with other data meeting the certification basis of the airplane that has been approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the EASA (or its delegated agent). Where Issue 6 of the ALI specifies to contact Airbus for appropriate action:
Before further flight, repair the damaged, cracked, or corroded structure using a method approved by either the Manager, International Branch, ANM-116, or the EASA (or its delegated agent).
(i) If any damage that exceeds the allowable limits specified in Issue 6 of the ALI is detected during any inspection required by this AD: At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, submit a report of the finding to Airbus, Customer Service Directorate, Attn: Department Manager Maintenance Engineering, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; e-mail: sched.maint@airbus.com. The report must include the ALI task reference, airplane serial number, the number of flight cycles and flight hours on the airplane, identification of the affected structure, location and description of the finding including its size and orientation, and the circumstance of detection and inspection method used. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501, et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
