Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A330-200 series airplanes. The DGAC advises that there have been several reported cases of fuel leaks in the fuel jettison system located on the wings. These leaks were observed during refueling and during maintenance. Inspection of the system revealed the presence of cracks and, in certain cases, breaks at the jettison valve. The inspection also revealed several partial disconnects of the valve inlet and/or outlet pipe. Analysis of the inspection data showed that the use of maximum tolerances in production when attaching the jettison valve to the wingbox bottom skin can cause cracks due to static overloading. These cracks can grow under the effect of fuel pressure loads during refueling operations and cause the valve to rupture. A ruptured valve could cause the fuel pipes to disconnect from the jettison valve and consequent fuel leaks from the fuel jettison outlets, which could result in fuel vapors coming into contact with ignition sources, and consequent fire or explosion.
Relevant Service Information
Airbus has issued Service Bulletin A330-57-3078, Revision 01, dated August 4, 2004. The service bulletin specifies that operators should discard any fuel jettison valve with certain serial numbers, or that has accumulated more than 5,200 flight cycles since it was first installed. The service bulletin describes procedures for doing a visual inspection for cracks of the external surfaces of the mounting flange of any remaining jettison valve, and an eddy current inspection for cracks if the visual inspection shows no cracks. If any crack is detected in the mounting flange during either inspection, the service bulletin specifies that the jettison valve should be removed and discarded. If no crack is detected after the eddy current inspection, the service bulletin specifies that the jettison valve may be re- installed. The service bulletin also describes procedures for modifying the diameters of the six attachment holes in the wing bottom skin panel before installing the same, uncracked, jettison valve after the inspections, or before installing a new jettison valve after the previous jettison valve has been discarded. The service bulletin also describes procedures for an operational test of the fuel jettison system to ensure that there are no fuel leaks. This test is done during the installation of the jettison valve.
Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F- 2004-127, dated August 4, 2004, to ensure the continued airworthiness of these airplanes in France.
The service bulletin refers to FR-HiTemp Service Bulletin HTE900169-28-1, Revision 1, dated November 8, 2004, as an additional source of service information for doing a visual inspection of the mounting flange of the jettison valve.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC's findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States.
Therefore, we are issuing this AD to prevent fuel leaks from the fuel jettison outlets. This AD requires accomplishing the actions specified in the service information described previously.
Clarification of Inspection Language
Although the French airworthiness directive specifies that operators "inspect visually" for cracks of the external surfaces of the mounting flange, this AD refers to that inspection a "detailed inspection." We have included the definition for a detailed inspection in a note in the AD.
Costs of Compliance
None of the airplanes affected by this action are on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future.
The following table provides the estimated costs to comply with this AD for any affected airplane that might be imported and placed on the U.S. Register in the future.
Estimated Costs
Action
Work hours
Average labor rate per hour
Parts cost
Cost per airplane
Inspection to determine serial number
1
$65
None
$65
Modification
13
$65
No Charge
845
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to the address listed under the ADDRESSES section. Include "Docket No. FAA- 2005-22483; Directorate Identifier 2004-NM-236-AD" at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it.
We will post all comments we receive, without change, to http://dms.dot.gov , including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://dms.dot.gov , or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647- 5227) islocated on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, "General requirements." Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that islikely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the National Government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the regulation:
1. Is not a "significant regulatory action" under Executive Order 12866;
2. Is not a "significant rule" under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See theADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by adding the following new airworthiness directive (AD):