Airworthiness Directives; Airbus Model A330-200 Series Airplanes, 56344-56347 [05-18910]

Download as PDF 56344 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations static torque loads. However, the size, configuration, and failure modes of jet engines have changed considerably from those envisioned when the engine seizure requirement of § 25.361(b) was first adopted. Current engines are much larger and are now designed with large bypass fans capable of producing much larger torque, if they become jammed. Relative to the engine configurations that existed when the rule was developed in 1957, the present generation of engines is sufficiently different and novel to justify issuance of special conditions to establish appropriate design standards. The latest generation of jet engines is capable of producing, during failure, transient loads that are significantly higher and more complex than those produced by the generation of engines in existence when the current regulation was developed. In order to maintain the level of safety envisioned in § 25.361(b), more comprehensive criteria are needed for the new generation of high bypass engines. The proposed special condition would distinguish between the more common failure events involving transient deceleration conditions with temporary loss of thrust capability and those rare events resulting from structural failures. Associated with these events, the proposed criteria establish design limit and ultimate load conditions. Discussion of Comments Notice of proposed special conditions No. 25–05–03–SC for the Airbus Model A318 airplanes equipped with Pratt and Whitney PW6000 engines, was published in the Federal Register on April 11, 2005 (70 CFR 18321). No comments were received. However, the FAA has reconsidered the inclusion of auxiliary power units in these special conditions. While § 25.361(b) is interpreted to apply to auxiliary power units, the novel or unusual design features identified above do not apply to them. Therefore, auxiliary power units are excluded from those special conditions and would continue to be treated under the current § 25.361(b). Except for the removal of auxiliary power units, these special conditions are adopted as proposed. Applicability As discussed above, these special conditions are applicable to Airbus Model A318–121 and A318–122 airplanes equipped with Pratt and Whitney PW6000 engines. Should Airbus apply at a later date for a change to the type certificate to include other type designs incorporating the same VerDate Aug<31>2005 14:40 Sep 26, 2005 Jkt 205001 novel or unusual design feature, these special conditions would apply to that model as well under the provisions of § 21.101. Condition This action affects certain novel or unusual design features on the Airbus Model A318 airplane equipped with Pratt and Whitney PW6000 engines. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Issued in Renton, Washington, on September 14, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–19206 Filed 9–26–05; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: [Docket No. FAA–2005–22483; Directorate Identifier 2004–NM–236–AD; Amendment 39–14292; AD 2005–19–27] Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. Airworthiness Directives; Airbus Model A330–200 Series Airplanes RIN 2120–AA64 The Special Conditions AGENCY: Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Airbus Model A318 airplane equipped with Pratt and Whitney PW6000 engines. For turbine engine installations other than auxiliary power units, in lieu of compliance with § 25.361(b), the following special condition applies: (a) The engine mounts, pylons and adjacent supporting airframe structure must be designed to withstand 1g level flight loads acting simultaneously with the maximum limit torque loads imposed by each of the following: (1) Sudden engine deceleration due to a malfunction which could result in a temporary loss of power or thrust. (2) The maximum acceleration of the engine. (b) For engine supporting structure, an ultimate loading condition must be considered that combines 1g flight loads with the transient dynamic loads resulting from each of the following: (1) The loss of any fan, compressor, or turbine blade. (2) Where applicable to a specific engine design, and separately from the conditions specified in paragraph (b)(1), any other engine structural failure that results in higher loads. (c) The ultimate loads developed from the conditions specified in paragraphs (b)(1) and (b)(2) above are to be multiplied by a factor of 1.0 when applied to engine mounts and pylons and multiplied by a factor of 1.25 when applied to adjacent supporting airframe structure. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330–200 series airplanes. This AD requires inspecting to determine the serial numbers and flight cycles of the fuel jettison valves and removing certain valves as applicable. This AD also requires doing a one-time inspection for cracks of the remaining jettison valves and removing any cracked valves. This AD also requires modifying the diameters of the six attachment holes in the wing bottom skin panel before installing a new or serviceable jettison valve. This AD results from reports of fuel leaks in the fuel jettison system located on the wings. We are issuing this AD to prevent fuel leaks from the fuel jettison outlets, which could result in fuel vapors coming into contact with ignition sources, and consequent fire or explosion. DATES: Effective October 12, 2005. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 12, 2005. We must receive comments on this AD by November 28, 2005. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. E:\FR\FM\27SER1.SGM 27SER1 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 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 56345 contact with ignition sources, and consequent fire or explosion. inspection of the mounting flange of the jettison valve. Relevant Service Information FAA’s Determination and Requirements of This AD 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 FRHiTemp Service Bulletin HTE900169– 28–1, Revision 1, dated November 8, 2004, as an additional source of service information for doing a visual 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 Inspection to determine serial number ........... Modification ..................................................... FAA’s Determination of the Effective Date No airplane affected by this AD is currently on the U.S. Register. VerDate Aug<31>2005 14:40 Sep 26, 2005 Jkt 205001 Average labor rate per hour 1 13 $65 65 Parts cost None ............................................................... No Charge ...................................................... Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Cost per airplane $65 845 less than 30 days after it is published in the Federal Register. E:\FR\FM\27SER1.SGM 27SER1 56346 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 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) is located 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. 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 is likely 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 the ADDRESSES 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701. 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 VerDate Aug<31>2005 14:40 Sep 26, 2005 Jkt 205001 § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–19–27 Airbus: Amendment 39–14292. Docket No. FAA–2005–22483; Directorate Identifier 2004–NM–236–AD. Effective Date (a) This AD becomes effective October 12, 2005. Affected ADs (b) None. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Applicability (c) This AD applies to Airbus Model A330– 201, –202, –203, –223, and –243 airplanes, certificated in any category; equipped with fuel jettison valve part number (P/N) HTE900169. Unsafe Condition (d) This AD results from reports of fuel leaks in the fuel jettison system located on the wings. We are issuing this AD to prevent fuel leaks from the fuel jettison outlets, which could result in fuel vapors coming into contact with ignition sources, and consequent fire or explosion. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin Reference (f) For the purposes of this AD the term ‘‘service bulletin’’ means the Accomplishment Instructions of Airbus Service Bulletin A330–57–3078, Revision 01, dated August 4, 2004. Note 1: The service bulletin refers to FRHiTemp 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. Inspection to Determine Serial Number and Flight Cycles (g) Within 40 months after the effective date of this AD, do the actions in paragraphs (g)(1) and (g)(2) of this AD in accordance with the service bulletin. (1) Inspect the fuel jettison valves, P/N HTE900169, to determine whether any of the following serial numbers are installed: FR092BC to FR099BC inclusive, FR001BD to FR030BD inclusive, FR031BE to FR058BE inclusive, and M151VB292. A review of airplane maintenance records is acceptable in lieu of this inspection if information can be conclusively determined from that review. If any affected serial number is installed: Before further flight, remove the jettison valve and do the modification in paragraph (i) of this AD. (2) Review airplane records to determine the number of flight cycles accumulated on the fuel jettison valves since first installation on the airplane. If any jettison valve has accumulated 5,200 total flight cycles or more, or if the number of flight cycles cannot be determined: Before further flight, remove the jettison valve and do the modification in paragraph (i) of this AD. Detailed and Eddy Current Inspections for Cracks of the Mounting Flange (h) Within 40 months after the effective date of this AD, for any jettison valve that was not removed in accordance with paragraph (g) of this AD, do a detailed inspection for cracks of the mounting flange of the jettison valve in accordance with the service bulletin. (1) If no crack is found during the detailed inspection: Before further flight, do an eddy current inspection for cracks of the mounting E:\FR\FM\27SER1.SGM 27SER1 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations flange of the jettison valve in accordance with the service bulletin and, whether a crack is found or not, before further flight, do the modification required by paragraph (i) of this AD. If no crack is found during the eddy current inspection, the inspected jettison valve may be reinstalled during the modification required by paragraph (i) of this AD. (2) If any crack is found during the detailed inspection: Before further flight, do the modification in paragraph (i) of this AD and do not reinstall the jettison valve. 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.’’ Modification (i) At the applicable time specified in paragraph (g) or (h) of this AD: Modify the diameters of the six attachment holes in the wing bottom skin panel, and install a new fuel jettison valve, or reinstall a previously installed fuel jettison valve that has been inspected and found to have no crack in accordance with paragraph (h) of this AD. Do all actions in accordance with the service bulletin. Parts Installation (j) As of the effective date of this AD, no person may install, on any airplane, a fuel jettison valve, P/N HTE900169, unless it has been inspected and had corrective actions done in accordance with paragraphs (g) and (h) of this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, ANM–116, Transport Airplane Directorate, FAA, 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 (l) French airworthiness directive F–2004– 127, dated August 4, 2004, also addresses the subject of this AD. Material Incorporated by Reference (m) You must use Airbus Service Bulletin A330–57–3078, Revision 01, dated August 4, 2004, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may VerDate Aug<31>2005 14:40 Sep 26, 2005 Jkt 205001 review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on September 15, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–18910 Filed 9–26–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22482; Directorate Identifier 2003–NM–009–AD; Amendment 39–14291; AD 2005–19–26] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model ATP Airplanes and Model HS 748 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model ATP airplanes and Model HS 748 airplanes. This AD requires doing a detailed inspection of the drain pipes of the fuel cross feed system and certain electrical cables for chafe damage; doing an inspection to determine the clearance between the cable loom and the cross feed drain pipe; and doing corrective actions if necessary. This AD results from a fire in the dry area of the wing due to severe chafe damage between an electrical cable and the fuel cross feed drain pipe. We are issuing this AD to prevent chafe damage of the electrical cable and fuel cross feed drain pipe that could lead to fuel leakage from the drain pipe and an ignition source from the electrical cable, which could result in a fire in the dry area of the airplane wing. DATES: This AD becomes effective October 12, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 12, 2005. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 56347 We must receive comments on this AD by November 28, 2005. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom, notified us that an unsafe condition may exist on all BAE Systems (Operations) Limited Model ATP airplanes and Model HS 748 airplanes. The CAA advises that an operator reported finding a fire in the dry area of the wing on a Model ATP airplane before takeoff. Severe chafe damage between an electrical cable and the drain pipe of the fuel cross feed system caused a small leakage of fuel from the drain pipe. Electrical sparks from the damaged electrical cable most likely ignited the fuel leakage. Chafe damage of the electrical cable and fuel cross feed drain pipe, if not prevented, could result in a fire in the dry area of the airplane wing. The fuel cross feed pipe drain on certain Model ATP airplanes is identical to those on the affected Model HS 748 airplanes. Therefore, all of these models may be subject to the same unsafe condition. Relevant Service Information BAE Systems (Operations) Limited has issued Alert Service Bulletin ATP– E:\FR\FM\27SER1.SGM 27SER1

Agencies

[Federal Register Volume 70, Number 186 (Tuesday, September 27, 2005)]
[Rules and Regulations]
[Pages 56344-56347]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18910]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22483; Directorate Identifier 2004-NM-236-AD; 
Amendment 39-14292; AD 2005-19-27]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A330-200 series airplanes. This AD requires 
inspecting to determine the serial numbers and flight cycles of the 
fuel jettison valves and removing certain valves as applicable. This AD 
also requires doing a one-time inspection for cracks of the remaining 
jettison valves and removing any cracked valves. This AD also requires 
modifying the diameters of the six attachment holes in the wing bottom 
skin panel before installing a new or serviceable jettison valve. This 
AD results from reports of fuel leaks in the fuel jettison system 
located on the wings. We are issuing this AD to prevent fuel leaks from 
the fuel jettison outlets, which could result in fuel vapors coming 
into contact with ignition sources, and consequent fire or explosion.

DATES: Effective October 12, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of October 12, 
2005.
    We must receive comments on this AD by November 28, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.

[[Page 56345]]

     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

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
----------------------------------------------------------------------------------------------------------------
                                                         Average labor                               Cost per
                Action                    Work hours     rate per hour         Parts cost            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.

[[Page 56346]]

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) is located 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 is likely 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 the ADDRESSES 
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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-19-27 Airbus: Amendment 39-14292. Docket No. FAA-2005-22483; 
Directorate Identifier 2004-NM-236-AD.

Effective Date

    (a) This AD becomes effective October 12, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-201, -202, -203, -223, 
and -243 airplanes, certificated in any category; equipped with fuel 
jettison valve part number (P/N) HTE900169.

Unsafe Condition

    (d) This AD results from reports of fuel leaks in the fuel 
jettison system located on the wings. We are issuing this AD to 
prevent fuel leaks from the fuel jettison outlets, which could 
result in fuel vapors coming into contact with ignition sources, and 
consequent fire or explosion.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin Reference

    (f) For the purposes of this AD the term ``service bulletin'' 
means the Accomplishment Instructions of Airbus Service Bulletin 
A330-57-3078, Revision 01, dated August 4, 2004.

    Note 1: 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.

Inspection to Determine Serial Number and Flight Cycles

    (g) Within 40 months after the effective date of this AD, do the 
actions in paragraphs (g)(1) and (g)(2) of this AD in accordance 
with the service bulletin.
    (1) Inspect the fuel jettison valves, P/N HTE900169, to 
determine whether any of the following serial numbers are installed: 
FR092BC to FR099BC inclusive, FR001BD to FR030BD inclusive, FR031BE 
to FR058BE inclusive, and M151VB292. A review of airplane 
maintenance records is acceptable in lieu of this inspection if 
information can be conclusively determined from that review. If any 
affected serial number is installed: Before further flight, remove 
the jettison valve and do the modification in paragraph (i) of this 
AD.
    (2) Review airplane records to determine the number of flight 
cycles accumulated on the fuel jettison valves since first 
installation on the airplane. If any jettison valve has accumulated 
5,200 total flight cycles or more, or if the number of flight cycles 
cannot be determined: Before further flight, remove the jettison 
valve and do the modification in paragraph (i) of this AD.

Detailed and Eddy Current Inspections for Cracks of the Mounting Flange

    (h) Within 40 months after the effective date of this AD, for 
any jettison valve that was not removed in accordance with paragraph 
(g) of this AD, do a detailed inspection for cracks of the mounting 
flange of the jettison valve in accordance with the service 
bulletin.
    (1) If no crack is found during the detailed inspection: Before 
further flight, do an eddy current inspection for cracks of the 
mounting

[[Page 56347]]

flange of the jettison valve in accordance with the service bulletin 
and, whether a crack is found or not, before further flight, do the 
modification required by paragraph (i) of this AD. If no crack is 
found during the eddy current inspection, the inspected jettison 
valve may be reinstalled during the modification required by 
paragraph (i) of this AD.
    (2) If any crack is found during the detailed inspection: Before 
further flight, do the modification in paragraph (i) of this AD and 
do not reinstall the jettison valve.

    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.''

Modification

    (i) At the applicable time specified in paragraph (g) or (h) of 
this AD: Modify the diameters of the six attachment holes in the 
wing bottom skin panel, and install a new fuel jettison valve, or 
reinstall a previously installed fuel jettison valve that has been 
inspected and found to have no crack in accordance with paragraph 
(h) of this AD. Do all actions in accordance with the service 
bulletin.

Parts Installation

    (j) As of the effective date of this AD, no person may install, 
on any airplane, a fuel jettison valve, P/N HTE900169, unless it has 
been inspected and had corrective actions done in accordance with 
paragraphs (g) and (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, ANM-116, Transport Airplane Directorate, 
FAA, 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 Sec.  
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

    (l) French airworthiness directive F-2004-127, dated August 4, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (m) You must use Airbus Service Bulletin A330-57-3078, Revision 
01, dated August 4, 2004, to perform the actions that are required 
by this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for a copy of this service information. You may review 
copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on September 15, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-18910 Filed 9-26-05; 8:45 am]
BILLING CODE 4910-13-P