Airworthiness Directive · Amendment 39-15051 · Airbus Model A300-600 Series Airplanes
Airbus Model A300-600 Series Airplanes
Superseded. A later AD replaced this one: AD 2007-10-10 R1. Comply with the one in force.
This AD applies to all Airbus Model A300-600 series airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections and critical design configuration control limitations (CDCCLs). Compliance with the operator maintenance documents 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 and CDCCLs, the operator may not be able to accomplish the inspections and CDCCLs 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 and CDCCLs that will preserve the critical ignition source prevention feature of the affected fuel system.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A300-600 series airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss 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, revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300-600 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A300-600 Fuel Airworthiness Limitations, Document 95A.1929/05, Issue 1, dated December 19, 2005 (approved by the European Aviation Safety Agency (EASA) on March 13, 2006), Section 1, “Maintenance/Inspection Tasks” (hereafter referred to as “Section 1 of Document 95A.1929/05”). For all tasks identified in Section 1 of Document 95A.1929/05, the initial compliance times start from the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1 of Document 95A.1929/05, except as provided by paragraph (g) of this AD.
(1) The effective date of this AD.
(2) The date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness.
Note 2: Airbus Operator Information Telex (OIT) SE 999.0076/06, dated June 20, 2006, identifies the applicable sections of the Airbus A300-600 airplane maintenance manual necessary for accomplishing the tasks specified in Section 1 of Document 95A.1929/05.
For Task 28-18-00-03-1, “Operational check of lo-level/underfull/calibration sensors,” identified in Section 1 of Document 95A.1929/05: The initial compliance time is the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD. Thereafter, Task 28-18-00-03-1 must be accomplished at the repetitive interval specified in Section 1 of Document 95A.1929/05.
(1) Prior to the accumulation of 40,000 total flight hours.
(2) Within 72 months or 20,000 flight hours after the effective date of this AD, whichever occurs first.
Within 12 months after the effective date of this AD, revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300-600 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A300-600 Fuel Airworthiness Limitations, Document 95A.1929/05, Issue 1, dated December 19, 2005 (approved by the EASA on March 13, 2006), Section 2, “Critical Design Configuration Control Limitations.”
(i) Except as provided by paragraph (j) of this AD: After accomplishing the actions specified in paragraphs (f) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
