Federal Aviation Administration January 16, 2008 – Federal Register Recent Federal Regulation Documents

We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

The FAA is superseding an existing airworthiness directive (AD), that applies to certain Airbus Model A310 series airplanes. That AD currently requires modification of certain wires in the right-hand (RH) wing. This new AD requires further modification by installing an additional protection sleeve and segregating route 2S in the RH pylon area. This AD results from analysis of wire routing that revealed that route 2S of the fuel electrical circuit, located in the RH wing, does not provide adequate separation of fuel quantity indication wires from wires carrying 115-volt alternating current (AC). We are issuing this AD to ensure that fuel quantity indication wires are properly separated from wires carrying 115-volt AC. Improper separation of such wires, in the event of wire damage, could lead to a short circuit and a possible ignition source, which could result in a fire in the airplane.

The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4 series airplanes; and all Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes. That AD currently requires repetitive inspections to detect cracking of the upper radius of the forward fitting of frame 47, and repair if necessary. This new AD retains those requirements, but reduces inspection thresholds and repetitive intervals, and adds related investigative and corrective actions. This AD also provides an optional terminating action for the repetitive inspections only for airplanes with cracking that is within certain limits, and a post-repair inspection program following the optional terminating action. This AD results from reports of additional cracking in airplanes that were inspected in accordance with the existing AD. We are issuing this AD to detect and correct fatigue cracking of the left and right upper radius at frame 47, which could propagate and result in reduced structural integrity of the airplane.