Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes, 37296-37302 [05-12839]

Download as PDF 37296 Federal Register / Vol. 70, No. 124 / Wednesday, June 29, 2005 / Proposed Rules applicable corrective actions. If any crack, corrosion, or damage is found during the open-hole high-frequency eddy current inspection specified in Boeing Special Attention Service Bulletin 747–28–2259, dated November 4, 2004: Before further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or in accordance with data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the approval must specifically reference this AD. (2) For Boeing Model 767–200, –300, –300F, and –400ER series airplanes: Rework the electrical bonding between the airplane structure and the pump housing of the override/jettison pumps in the left and right wing center auxiliary fuel tanks, and do the related investigative and applicable corrective actions. Alternative Methods of Compliance (AMOCs) (g) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on June 21, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12840 Filed 6–28–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21702; Directorate Identifier 2005–NM–024–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A330 and A340 series airplanes. This proposed AD would require repetitive borescope inspections of the left and right fuel tanks of the trimmable horizontal stabilizers (trim tanks) for detached or damaged float valves; related investigative/corrective actions if necessary; and the eventual replacement of all float valves in the left and right VerDate jul<14>2003 15:26 Jun 28, 2005 Jkt 205250 trim tanks with new, improved float valves, which terminates the need for the repetitive inspections. This proposed AD would also require repetitive replacement of certain new, improved float valves. This proposed AD is prompted by reports of detached and damaged float valves in the trim tanks. We are proposing this AD to prevent, in the event of a lightning strike to the horizontal stabilizer, sparking of metal parts and debris from detached and damaged float valves, or a buildup of static electricity, which could result in ignition of fuel vapors and consequent fire or explosion. DATES: We must receive comments on this proposed AD by July 29, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed 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. • By 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. For service information identified in this proposed AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can examine the contents of this AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 21702; the directorate identifier for this docket is 2005–NM–024–AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 2005–21702; Directorate Identifier 2005–NM–024–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. 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 proposed AD. Using the search function of our docket 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 can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit http:// dms.dot.gov. Examining the Docket You can 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 DMS receives them. Discussion We have examined the underlying safety issues involved in recent fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (67 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design approval E:\FR\FM\29JNP1.SGM 29JNP1 Federal Register / Vol. 70, No. 124 / Wednesday, June 29, 2005 / Proposed Rules (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design approval holders for large turbinepowered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: single failures, single failures in combination with another latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. The Joint Aviation Authorities (JAA) has issued a regulation that is similar to SFAR 88. (The JAA is an associated body of the European Civil Aviation Conference (ECAC) representing the civil aviation regulatory authorities of a number of European States who have agreed to co-operate in developing and implementing common safety regulatory standards and procedures.) Under this regulation, the JAA stated that all members of the ECAC that hold type certificates for transport category airplanes are required to conduct a design review against explosion risks. We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. ´ ´ 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 and A340 series airplanes. The DGAC advises that it has received reports of detached and damaged float valves in the left and right fuel tanks of the 37297 trimmable horizontal stabilizers (trim tanks). The left tank float valves, part number (P/N) L87–13–001, are manufactured by Intertechnique. The right tank float valves, P/N 61600, are manufactured by Argo-Tech. The float valves are part of the fuel vent system. The DGAC states that the affected float valves detached as a result of environmental fatigue that exceeded the valves’ qualification standards. Certain float valves have metal parts which, when detached and positioned in certain locations/orientations in the trim tank, may create ignition sources in the trim tanks. If there is a lightning strike to the horizontal stabilizer, the metal parts and debris from detached and damaged float valves may cause sparking, or a buildup of static electricity, which could result in ignition of fuel vapors and consequent fire or explosion. The DGAC also advises that a life limit of 24,500 flight cycles must be imposed on Intertechnique vent float valves, P/N L87–13–002, if installed in the left trim tank on Model A330 series airplanes. Relevant Service Information Airbus has issued the following service bulletins: RELEVANT SERVICE INFORMATION Airbus model Airbus service bulletin A330 series airplanes ............................................................................... A340–200 and –300 series airplanes ...................................................... A340–541 and –642 airplanes ................................................................. Service Bulletins A330–28–3086 and A340–28–4100, Revision 01, include procedures for performing repetitive borescope inspections of the right trim tank for detached or damaged float valves, and related investigative/ corrective actions if necessary. Service Bulletins A330–28–3087 and A340–28– 4101, both Revision 01, include procedures for doing those same actions for the left trim tank. If a float valve is detached, or the arms are damaged, the related investigative/corrective actions include: • Doing a detailed visual inspection for damage to the trim tank structure; VerDate jul<14>2003 15:26 Jun 28, 2005 Jkt 205250 A330–28–3086, A330–28–3087, A330–28–3088, A330–28–3089, A330–28–3094, A340–28–4100, A340–28–4101, A340–28–4102, A340–28–4103, A340–28–4111, A340–28–5007, A340–28–5010, A340–28–5021, dated July 24, 2003. Revision 01, dated August 16, 2004. dated April 27, 2004. Revision 02, dated April 1, 2005. dated April 7, 2005. Revision 01, dated August 16, 2004. Revision 01, dated August 16, 2004. dated April 27, 2004. Revision 02, dated April 1, 2005. dated April 6, 2005. May 7, 2004. May 7, 2004. dated April 6, 2005. • Repairing structural damage in accordance with the applicable Airbus Structural Repair Manual (SRM) and contacting Airbus if the damage exceeds the limits specified in the SRM; • Removing a detached float valve and associated debris from the trim tank; • Replacing the float valve; and • Reporting all findings to Airbus. These service bulletins also provide the option of deactivating an affected trim tank until the float valve can be replaced in accordance with the operator’s maintenance schedule. In addition, for airplanes on which some PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 floats are intact, Service Bulletin A340– 28–4100, Revision 01, provides the option of contacting Airbus for the possible issuance of an Airbus No Technical Objection (NTO) letter to allow continued operation, for a specified number of flight cycles, without deactivating the trim tank. Service Bulletins A330–28–3088, A340–28–4102, and A340–28–5007 include procedures for installing a new, improved float valve, P/N 62015–1, manufactured by Argo-Tech, in the right trim tank. The installation procedures include: E:\FR\FM\29JNP1.SGM 29JNP1 37298 Federal Register / Vol. 70, No. 124 / Wednesday, June 29, 2005 / Proposed Rules • Removing the existing float valve and bonding leads; • Removing a detached float valve and associated debris from the trim tank, if necessary; • Repairing structural damage in accordance with the applicable Airbus Structural Repair Manual (SRM) and contacting Airbus if the damage exceeds the limits specified in the SRM; • Preparing the airplane structure to accommodate the new electrical bonding; • Installing P/N 62015–1; and • Performing a bonding test of the float valve. Service Bulletin A330–28–3088 also specifies a life limit of 20,000 flight cycles since first installation for the new Argo-Tech float valve, P/N 62015–1. Service Bulletins A330–28–3088 and A340–28–4102 state that any removed float valve having a certain part number should be sent to Argo-Tech. In addition, Service Bulletin A330–28– 3088 identifies Airbus Service Bulletin A330–55–3022, dated November 4, 1997, as a concurrent service bulletin; and Service Bulletin A340–28–4102 identifies Airbus Service Bulletin A340– 55–4023, dated November 4, 1997, as a concurrent service bulletin. The concurrent service bulletins include procedures for installing Teflon gore joints in the front spar panels. Service Bulletin A330–28–3088 states that accomplishing the actions specified in that service bulletin cancels the inspections specified in Service Bulletin A330–28–3086. Service Bulletin A340– 28–4102 states that accomplishing the actions specified in that service bulletin cancels the inspections specified in Service Bulletin A340–28–4100. Procedures for installing a new, improved float valve, P/N L87–13–002, manufactured by Intertechnique, in the left trim tank, are included in the following service bulletins: A330–28– 3089, Revision 02; A340–28–4103, Revision 02; and A340–28–5010. The installation procedures include: • Removing the existing float valve; • Removing a detached float valve and associated debris from the trim tank, if necessary; • Repairing structural damage in accordance with the applicable Airbus Structural Repair Manual (SRM) and contacting Airbus for damage that exceeds the limits specified in the SRM; • Installing P/N L87–13–002; and • Performing a bonding test of the float valve. Service Bulletin A330–28–3089, Revision 02, also specifies a life limit of 24,500 flight cycles since first installation for the new Intertechnique VerDate jul<14>2003 15:26 Jun 28, 2005 Jkt 205250 float valve, P/N L87–13–002. Service Bulletins A330–28–3089, Revision 02; A340–28–4103, Revision 02; and A340– 28–5010 also state that removed float valves having a certain part number should be sent to Intertechnique. In addition, Service Bulletin A330–28– 3089 identifies Airbus Service Bulletin A330–55–3022 as a concurrent service bulletin; and Service Bulletin A340–28– 4103 identifies Airbus Service Bulletin A340–55–4023 as a concurrent service bulletin. Service Bulletin A330–28–3089, Revision 02, states that accomplishing the actions in that service bulletin cancels the inspections specified in Service Bulletin A330–28–3087. Service Bulletin A340–28–4103, Revision 02, states that accomplishing the actions in that service bulletin cancels the inspections specified in Service Bulletin A340–28–4101. Procedures for installing a new, improved float valve, P/N L87–13–003, manufactured by Intertechnique, in the left trim tank, are included in the following service bulletins: A330–28– 3094, A340–28–4111, and A340–28– 5021. The installation procedures include: • Removing the existing float valve; • Removing a detached float valve and associated debris from the trim tank, if necessary; • Repairing structural damage in accordance with the applicable Airbus Structural Repair Manual (SRM) and contacting Airbus for damage that exceeds the limits specified in the SRM; • Installing P/N L87–13–003; and • Performing a bonding test of the float valve. Service Bulletin A330–28–3094 states that, if P/N L87–13–002 has not been installed, accomplishing the actions specified in that service bulletin eliminates the need for accomplishing the actions specified in Service Bulletin A330–28–3089. Service Bulletin A340– 28–4111 states that, if P/N L87–13–002 has not been installed, accomplishing the actions specified in that service bulletin eliminates the need for accomplishing the actions specified in Service Bulletin A340–28–4103. Service Bulletin A340–28–5021 states that, if P/N L87–13–002 has not been installed, accomplishing the actions specified in that service bulletin eliminates the need for accomplishing the actions specified in Service Bulletin A340–28–5010. The DGAC mandated the service information and issued French airworthiness directives F–2005–003, dated January 5, 2005, and F–2005–004 R1 and F–2005–005 R1, both dated April 27, 2005, to ensure the continued PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are 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 proposing this AD, which would require repetitive borescope inspections of the left and right fuel tanks of the trimmable horizontal stabilizers (trim tanks) for detached or damaged float valves; related investigative/corrective actions if necessary; and the eventual replacement of all float valves in the left and right trim tanks with new, improved float valves, which terminates the need for the repetitive inspections. This proposed AD would also require repetitive replacement of certain new, improved float valves. Differences Among the Proposed AD, French Airworthiness Directives, and Service Information All of the service bulletins specify that if the structural damage caused by a detached float exceeds the limits in the applicable Airbus SRM, you may contact the manufacturer for instructions on how to repair the damage. This proposed AD would require you to contact us, or the DGAC (or its delegated agent), for instructions on how to repair damage that exceeds the limits in the SRM. Also, this proposed AD provides the option of either repairing any structural damage in accordance with the applicable service bulletin, or in accordance with a method approved by us, or the DGAC (or its delegated agent). In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the DGAC approve would be acceptable for compliance with this proposed AD. Service Bulletin A340–28–4100, Revision 01, provides operators the option of contacting Airbus for the possible issuance of an Airbus NTO E:\FR\FM\29JNP1.SGM 29JNP1 37299 Federal Register / Vol. 70, No. 124 / Wednesday, June 29, 2005 / Proposed Rules letter to allow continued operation without deactivating the trim tank for a specified number of flight cycles. This proposed AD would not allow that action. We can better ensure long-term continued operational safety by having operators correct the source of the problem, the trim tank. Anyone may apply for an AMOC and make a request to temporarily operate an airplane without a deactivated trim tank. Operators should note that, although the Accomplishment Instructions of certain referenced service bulletins describe procedures for submitting an inspection report sheet to Airbus, or returning removed float valves to the float valve manufacturer, this proposed AD would not require those actions. Concurrent Service Information Airbus Service Bulletins A330–28– 3088 and A330–28–3089 identify Airbus Service Bulletin A330–55–3022 as a concurrent service bulletin, and Airbus Service Bulletins A340–28–4102 and A340–28–4103 identify Airbus Service Bulletin A340–55–4023 as a concurrent service bulletin. The concurrent service bulletins include procedures for installing Teflon gore joints on front spar access panel 343ER. That action reduces the number of work hours needed to remove and install the access panel when the new, improved float valves are installed. The French airworthiness directives do not mandate accomplishment of the concurrent service bulletins and this proposed AD would not require accomplishment of the concurrent service bulletins. necessary. The DGAC has informed us that it does not intend to issue a parallel French airworthiness directive for Airbus Model A340 series airplanes. The DGAC states that a float valve life limit of 24,500 flight cycles is above the A340 design service goal of 20,000 flight cycles. Intertechnique float valve, P/N L87–13–003, did not exhibit any failure during qualification tests and does not have a life limit for Airbus Model A330 or A340 series airplanes. Clarification of Life Limit in Paragraph (h) of the Proposed AD In this proposed AD, the ‘‘detailed visual inspection’’ specified in the Airbus service bulletins is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in Note 1 of this AD. For Airbus Model A330 series airplanes, French airworthiness directive F–2005–003, dated January 5, 2005, mandates a life limit of 24,500 flight cycles ‘‘since new’’ for Intertechnique float valve, P/N L87–13– 002. This P/N failed in a mode that potentially re-introduced the possible ignition source, so a life limit is Clarification of Inspection Terminology Costs of Compliance The following table provides the estimated costs for U.S. operators of Model A330 series airplanes to comply with this proposed AD. ESTIMATED COSTS Average labor rate per hour Number of U.S.-registered airplanes Cost per airplane Action Work hours Borescope inspection, per inspection cycle. Installation of float valves. 2 (1 hour per float, 2 floats per airplane). $65 None ......................... $130 25 $3,250, per inspection cycle. 4 (2 per valve, 2 valves per airplane). 1 ............................... 65 No charge ................ 260 25 $6,500, per installation. 65 None ......................... 65 25 $1,625. Bonding test (new, improved float valves, left trim tank only). Currently, there are no affected Model A340 series airplanes on the U.S. Register. However, should an affected airplane be imported and placed on the U.S. Register in the future, it would be subject to the proposed actions of this AD. The estimated costs would be the same as those listed above for the Model A330 series airplanes. 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 VerDate jul<14>2003 15:26 Jun 28, 2005 Jkt 205250 Parts 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Fleet cost 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 proposed AD. 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: E:\FR\FM\29JNP1.SGM 29JNP1 37300 Federal Register / Vol. 70, No. 124 / Wednesday, June 29, 2005 / Proposed Rules § 39.13 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. Affected ADs [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–21702; Directorate Identifier 2005–NM–024–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by July 29, 2005. (b) None. Applicability (c) This AD applies to Airbus Model A330 and A340 series airplanes, certificated in any category, as identified in Table 1 of this AD. TABLE 1.—APPLICABILITY Airbus model Except those modified in production by airbus modification A330 series airplanes ............................................................................... A340–200 and –300 series airplanes ...................................................... A340–541 and –642 airplanes ................................................................. Unsafe Condition (d) This AD was prompted by reports of detached and damaged float valves in the left and right fuel tanks of the trimmable horizontal stabilizers (trim tanks). We are issuing this AD to prevent, in the event of a lightning strike to the horizontal stabilizer, sparking of metal parts and debris from detached and damaged float valves, or a buildup of static electricity, which could result in ignition of fuel vapors and consequent fire or explosion. Compliance (e) You are responsible for having the actions required by this AD performed within 51953 and either 52110 or 53081 51953 and either 52110 or 53081 51951 and either 52109 or 53081 the compliance times specified, unless the actions have already been done. Borescope Inspection (f) At the later of the times specified in paragraph (f)(1) and (f)(2) of this AD: Do a borescope inspection for detached or damaged float valves in the left and right trim tanks, by doing the applicable actions in the Accomplishment Instructions of Airbus Service Bulletins A330–28–3086, dated July 24, 2003; and A330–28–3087, Revision 01, dated August 16, 2004 (for Model A330 series airplanes); or A340–28–4100 and A340–28– 4101, both Revision 01, both dated August 16, 2004 (for Model A340–200 and –300 series airplanes); as applicable. (1) Prior to the accumulation of 2,500 total flight cycles or 15,000 total flight hours, whichever is first. (2) Within 7,500 flight hours after the effective date of this AD. Related Investigative and Corrective Actions (g) Depending on the results of the inspection required by paragraph (f) of this AD: Do the applicable actions in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD, at the times specified in Table 2. TABLE 2.—INSPECTION RESULTS AND RELATED INVESTIGATIVE/CORRECTIVE ACTIONS If inspection results reveal— Then— In accordance with Airbus Service Bulletin— Detached or damaged float valve in the right trim tank. Before further flight: (1) Remove the detached float and float debris from the trim tank and do a detailed inspection for structural damage to the affected trim tank tank. Repair any structural damage to the trim tank or deactivate the trim tank, before further flight, in accordance with the applicable service bulletin, or in accordance with a method approved by the Manager, International Branch, ANM– ´ ´ 116, FAA, Transport Airplane Directorate; or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). Where the service bulletin specifies to contact the manufacturer, instead contact the Manager, International Branch, ANM–116, or the DGAC (or its delegated agent). Before further flight, after doing the detailed inspection and repairing any structural damage: (2) Replace the affected float valve with a new unit having the same part number (P/N), or a new, improved float valve, P/N 62015–1. If a new unit of P/N 61600 is installed, thereafter, do the inspection required by paragraph (f) of this AD at intervals not to exceed 2,500 flight cycles or 15,000 flight hours, whichever is first, after the most recent inspection, until paragraph (h) of this AD is accomplished. A330–28–3086, dated July 24, 2003. A340–28–4100, Revision 01, dated August 16, 2004. Detached or damaged float valve in the left trim tank. VerDate jul<14>2003 15:26 Jun 28, 2005 Before further flight: (1) Remove the detached float and float debris from the trim tank and do a detailed inspection for structural damage to the affected trim tank. Repair any structural damage to the trim tank or deactivate the trim tank, before further flight, in accordance with the applicable service bulletin, or in accordance with a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent). Where the service bulletin specifies to contact the manufacturer, instead contact the Manager, International Branch, ANM–116, or the DGAC (or its delegated agent). Jkt 205250 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\29JNP1.SGM 29JNP1 A330–28–3086, dated July 24, 2003. A330–28–3088, dated April 27, 2004. A340–28–4100, Revision 01, dated August 16, 2004. A340–28–4102, dated April 27, 2004. A330–28–3087, Revision 01, dated August 16, 2004. A340–28–4101, Revision 01, dated August 16, 2004. Federal Register / Vol. 70, No. 124 / Wednesday, June 29, 2005 / Proposed Rules 37301 TABLE 2.—INSPECTION RESULTS AND RELATED INVESTIGATIVE/CORRECTIVE ACTIONS—Continued Then— In accordance with Airbus Service Bulletin— Before further flight, after doing the detailed inspection and repairing any structural damage: (2) Replace the affected float valve with either a new unit having that same P/N, or a new improved float valve, P/N L87–13–002 or P/N L87–13–003. If a new unit of P/N L87–13–001 is installed, thereafter, do the inspection required by paragraph (f) of this AD at intervals not to exceed 2,500 flight cycles or 15,000 flight hours, whichever is first, after the most recent inspection, until paragraph (h) of this AD is accomplished. For Airbus Model A330 series airplanes, if a float valve having P/N L87–13–002 is installed, thereafter, replace that float valve with a float valve having that same P/N at intervals not to exceed those specified in paragraph (h) of this AD. Installation of P/N L87–13–003 on Airbus Model A330 series airplanes terminates the repetitive float valve replacement required by paragraph (h) of this AD. A330–28–3087, Revision 01, dated August 16, 2004. A330–28–3089, Revision 02, dated April 1, 2005. A330–28–3094, dated April 7, 2005. A340–28–4101, Revision 01, dated August 16, 2004. A340–28–4103, Revision 02, dated April 1, 2005. A340–28–4111, dated April 6, 2005. A330–28–3086, dated July 24, 2003. A330–28–3088, dated April 27, 2004. A340–28–4100, Revision 01, dated August 16, 2004. A340–28–4102, dated April 27, 2004. A330–28–3087, Revision 01, August 16, 2004. A330–28–3089, Revision 02, dated April 1, 2005. A330–28–3094, dated April 7, 2005. A340–28–4101, Revision 01, dated August 16, 2004. A340–28–4103, Revision 02, dated April 1, 2005. A340–28–4111, dated April 6, 2005. If inspection results reveal— No damaged or detached float valve in the right trim tank. Within 10,000 flight hours or 1,500 flight cycles, whichever is first, from the initial float inspection done in accordance with paragraph (f) of this AD, replace the existing Argo-new Tech float valve, P/N 61600, with either a unit having that same P/N, or a new, improved float valve, P/N 62015–1. If a new unit of P/N 61600 is installed, thereafter, repeat the inspection required by paragraph (f) of this AD at intervals not to exceed 2,500 flight cycles or 15,000 flight hours, whichever is first, until paragraph (h) of this AD is accomplished. No damaged detached float valve in the left trim tank. Within 10,000 flight hours or 1,500 flight cycles, whichever is first, from the initial inspection done in accordance with paragraph (f) of this AD, replace the existing trim tank Intertechnique float valve, P/N L87–13–001, with either a new unit having that same P/N, or a new improved float valve, P/N L87–13–002 or P/N L87– 13–003. If a new unit of P/N L87–13–001 is installed, thereafter, do the inspection required by paragraph (f) of this AD at intervals not to exceed 2,500 flight cycles or 15,000 flight hours, whichever is first, after the most recent inspection, until paragraph (h) of this AD is accomplished. For Airbus Model A330 series airplanes, if a float valve having P/N L87–13–002 is installed, thereafter, replace that float valve with a float valve having that same P/N at intervals not to exceed those specified in paragraph (h) of this AD. Installation of P/N L87–13–003 on Airbus Model A330 series airplanes terminates the repetitive float valve replacement required by paragraph (h) of this AD. 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.’’ Installation of New, Improved Float Valves (h) Within 50 months after the effective date of this AD: Replace any Argo-Tech float valve, P/N 61600, with a new, improved float valve, P/N 62015–1; replace any Intertechnique float valve, P/N L87–13–001, with a new, improved float valve, P/N L87– 13–002 or P/N L87–13–003; and do any applicable corrective action; by accomplishing the actions specified in the Accomplishments Instructions of the applicable service bulletin in Table 3 of this AD. Do any applicable corrective action before further flight. For Airbus Model A330 series airplanes, if P/N L87–13–002 is installed, replace the float valve thereafter at intervals not to exceed 24,500 flight cycles. Installation of P/N L87–13–003 on Airbus Model A330 series airplanes terminates the repetitive float valve replacement required by this paragraph. Installation of either P/N L87–13–002 or P/N L87–13–003 terminates the borescope inspections required by paragraphs (f) and (g) of this AD. Where the service bulletin specifies to contact the manufacturer, instead contact the Manager, International Branch, ANM–116, or the DGAC (or its delegated agent). TABLE 3.—SERVICE INFORMATION FOR NEW FLOAT VALVES Airbus model Float valve P/N A330 series airplanes ..................... 62015–1 ......................................... L87–13–002 ................................... L87–13–003 ................................... 62015–1 ......................................... L87–13–002 ................................... L87–13–003 ................................... 62015–1 ......................................... L87–13–002 ................................... L87–13–003 ................................... 340–200 and –300 series airplanes A340–541 and –642 airplanes ........ VerDate jul<14>2003 15:26 Jun 28, 2005 Jkt 205250 PO 00000 Frm 00011 Fmt 4702 Airbus service bulletin A330–28–3088, A330–28–3089, A330–28–3094, A340–28–4102, A340–28–4103, A340–28–4111, A340–28–5007, A340–28–5010, A340–28–5021, Sfmt 4702 dated April 27, 2004. Revision 02, dated April 1, 2005. dated April 7, 2005. dated April 27, 2004. Revision 02, dated April 1, 2005. dated April 6, 2005. dated May 7, 2004. dated May 7, 2004. dated April 6, 2005. E:\FR\FM\29JNP1.SGM 29JNP1 37302 Federal Register / Vol. 70, No. 124 / Wednesday, June 29, 2005 / Proposed Rules Actions Accomplished Previously (i) Inspections and related investigative and corrective actions accomplished before the effective date of this AD, in accordance with any applicable Airbus service bulletin identified in Table 4 of this AD, are acceptable for compliance with the corresponding actions specified in this AD. TABLE 4.—SERVICE INFORMATION FOR ACTIONS ACCOMPLISHED PREVIOUSLY Airbus model A330 series airplanes. A340–200 and –300 series airplanes. Airbus service bulletin A330–28–3087, dated July 24, 2003. A330–28–3089, Revision 01, dated May 12, 2004. A340–28–4100, dated July 24, 2003. A340–28–5010, dated May 7, 2004. A340–28–5021, dated April 6, 2005. No Submission of Information/Parts (j) Where any Airbus service bulletin specifies to submit information to Airbus, or send removed float valves to either ArgoTech or Intertechnique, those actions are not required by this AD. Alternative Methods of Compliance (AMOCs) (k) The Manager, International Branch, 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. Related Information (l) French airworthiness directives F– 2005–003, dated January 5, 2005, and F– 2005–004 R1 and F–2005–005 R1, both dated April 27, 2005, also address the subject of this AD. Issued in Renton, Washington, on June 22, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12839 Filed 6–28–05; 8:45 am] BILLING CODE 4910–13–P required under sections 612(a)(23)(A) and 674(e)(4) of the Individuals with Disabilities Education Act, as amended by the Individuals with Disabilities Education Improvement Act of 2004 (Act). The purpose of the NIMAS is to help increase the availability and timely delivery of print instructional materials in accessible formats to blind or other persons with print disabilities in elementary schools and secondary schools. We must receive your comments on or before September 12, 2005. ADDRESSES: Address all comments about this proposed standard to Troy Justesen, Office of Special Education and Rehabilitative Services, U.S. Department of Education, 400 Maryland Avenue, SW., room 5126, Potomac Center Plaza, Washington, DC 20202–2641. If you prefer to send your comments through the Internet, you may address them to us at the U.S. Government Web site: http://www.regulations.gov. Or you may send your Internet comments to us at the following address: Osersnimascomments@ed.gov. You must include the term ‘‘NIMAS Comments’’ in the subject line of your electronic message. Please submit your comments only one time in order to ensure that we do not receive duplicate copies. FOR FURTHER INFORMATION CONTACT: Troy R. Justesen. Telephone: (202) 245–7468. If you use a telecommunications device for the deaf (TDD), you may call the Federal Relay Service (FRS) at 1– 800–877–8339. Individuals with disabilities may obtain this document in an alternative format (e.g., Braille, large print, audiotape, or computer diskette) on request to the contact person listed under FOR FURTHER INFORMATION CONTACT. DATES: SUPPLEMENTARY INFORMATION: Invitation to Comment DEPARTMENT OF EDUCATION 34 CFR Part 300 RIN 1820–AB56 National Instructional Materials Accessibility Standard Office of Special Education and Rehabilitative Services, Department of Education. ACTION: Notice of proposed rulemaking. AGENCY: SUMMARY: The Secretary of Education proposes to establish the National Instructional Materials Accessibility Standard (NIMAS or standard) as VerDate jul<14>2003 15:26 Jun 28, 2005 Jkt 205250 We invite you to submit comments regarding our proposal to adopt the NIMAS and to make your comments as specific as possible. Also, if appropriate, please identify the specific section or subsection of the NIMAS that each of your comments addresses and arrange your comments in the same order as the standard. We invite you to assist us in complying with the specific requirements of Executive Order 12866 and its overall requirement of reducing regulatory burden that might result from this proposed regulatory action. Please let us know of any further opportunities we should take to reduce potential costs PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 or increase potential benefits in connection with this regulatory action. Please include the following with your comments: A description of the area of your involvement in special education or regular education, as well as your role, if any, in that area (e.g., parent, teacher, student, state or local administrator, or researcher) or other area (e.g., technology specialist, publisher, or software developer). During and after the comment period, you may inspect all public comments about the standard in room 5126, Potomac Center Plaza, 550 12th Street, SW., Washington, DC, between the hours of 8:30 a.m. and 4 p.m., Eastern time, Monday through Friday of each week except Federal holidays. Assistance to Individuals With Disabilities in Reviewing the Comments On request, we will supply an appropriate aid, such as a reader or print magnifier, to an individual with a disability who needs assistance to review the comments or other documents in the public rulemaking record for this standard. If you want to schedule an appointment for this type of aid, please contact the person listed under FOR FURTHER INFORMATION CONTACT. Background States use electronic files from publishers of educational materials to produce accessible versions (e.g., Braille or digital audio) of these materials or contract to have accessible versions produced from these files. Because States have different requirements for these electronic files, however, publishers often experience increased costs for production, and States experience delays and inconsistencies in the materials produced. To facilitate the provision of accessible, timely, and consistent versions of print textbooks in the United States, the Department of Education funded the National Center on Accessing the General Curriculum (NCAC) at the Center on Applied Special Technologies, Inc. (CAST) to establish technical specifications for a voluntary national instructional materials accessibility standard. Beginning in November 2002, NCAC convened a panel of 43 experts, composed of educators, publishers, technology specialists, and disability groups. The National Institute of Standards and Technology (NIST) also participated on the panel. The panel held three public meetings in January, March, and June 2003, and conducted extensive teleconference and online discussions. E:\FR\FM\29JNP1.SGM 29JNP1

Agencies

[Federal Register Volume 70, Number 124 (Wednesday, June 29, 2005)]
[Proposed Rules]
[Pages 37296-37302]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12839]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21702; Directorate Identifier 2005-NM-024-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 and A340 Series 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A330 and A340 series airplanes. This proposed 
AD would require repetitive borescope inspections of the left and right 
fuel tanks of the trimmable horizontal stabilizers (trim tanks) for 
detached or damaged float valves; related investigative/corrective 
actions if necessary; and the eventual replacement of all float valves 
in the left and right trim tanks with new, improved float valves, which 
terminates the need for the repetitive inspections. This proposed AD 
would also require repetitive replacement of certain new, improved 
float valves. This proposed AD is prompted by reports of detached and 
damaged float valves in the trim tanks. We are proposing this AD to 
prevent, in the event of a lightning strike to the horizontal 
stabilizer, sparking of metal parts and debris from detached and 
damaged float valves, or a buildup of static electricity, which could 
result in ignition of fuel vapors and consequent fire or explosion.

DATES: We must receive comments on this proposed AD by July 29, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed 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.
     By 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.
    For service information identified in this proposed AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-21702; the directorate identifier for this docket is 
2005-NM-024-AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-21702; 
Directorate Identifier 2005-NM-024-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    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 proposed AD. Using the search function of our 
docket 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 can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can 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 DMS receives them.

Discussion

    We have examined the underlying safety issues involved in recent 
fuel tank explosions on several large transport airplanes, including 
the adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design approval

[[Page 37297]]

(i.e., type certificate (TC) and supplemental type certificate (STC)) 
holders to substantiate that their fuel tank systems can prevent 
ignition sources in the fuel tanks. This requirement applies to type 
design approval holders for large turbine-powered transport airplanes 
and for subsequent modifications to those airplanes. It requires them 
to perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with another latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    The Joint Aviation Authorities (JAA) has issued a regulation that 
is similar to SFAR 88. (The JAA is an associated body of the European 
Civil Aviation Conference (ECAC) representing the civil aviation 
regulatory authorities of a number of European States who have agreed 
to co-operate in developing and implementing common safety regulatory 
standards and procedures.) Under this regulation, the JAA stated that 
all members of the ECAC that hold type certificates for transport 
category airplanes are required to conduct a design review against 
explosion risks.
    We have determined that the actions identified in this proposed AD 
are necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    The Direction G[eacute]n[eacute]rale 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 and A340 series 
airplanes. The DGAC advises that it has received reports of detached 
and damaged float valves in the left and right fuel tanks of the 
trimmable horizontal stabilizers (trim tanks). The left tank float 
valves, part number (P/N) L87-13-001, are manufactured by 
Intertechnique. The right tank float valves, P/N 61600, are 
manufactured by Argo-Tech. The float valves are part of the fuel vent 
system. The DGAC states that the affected float valves detached as a 
result of environmental fatigue that exceeded the valves' qualification 
standards. Certain float valves have metal parts which, when detached 
and positioned in certain locations/orientations in the trim tank, may 
create ignition sources in the trim tanks. If there is a lightning 
strike to the horizontal stabilizer, the metal parts and debris from 
detached and damaged float valves may cause sparking, or a buildup of 
static electricity, which could result in ignition of fuel vapors and 
consequent fire or explosion.
    The DGAC also advises that a life limit of 24,500 flight cycles 
must be imposed on Intertechnique vent float valves, P/N L87-13-002, if 
installed in the left trim tank on Model A330 series airplanes.

Relevant Service Information

    Airbus has issued the following service bulletins:

                      Relevant Service Information
------------------------------------------------------------------------
              Airbus model                   Airbus service bulletin
------------------------------------------------------------------------
A330 series airplanes..................  A330-28-3086, dated July 24,
                                          2003.
                                         A330-28-3087, Revision 01,
                                          dated August 16, 2004.
                                         A330-28-3088, dated April 27,
                                          2004.
                                         A330-28-3089, Revision 02,
                                          dated April 1, 2005.
                                         A330-28-3094, dated April 7,
                                          2005.
A340-200 and -300 series airplanes.....  A340-28-4100, Revision 01,
                                          dated August 16, 2004.
                                         A340-28-4101, Revision 01,
                                          dated August 16, 2004.
                                         A340-28-4102, dated April 27,
                                          2004.
                                         A340-28-4103, Revision 02,
                                          dated April 1, 2005.
                                         A340-28-4111, dated April 6,
                                          2005.
A340-541 and -642 airplanes............  A340-28-5007, May 7, 2004.
                                         A340-28-5010, May 7, 2004.
                                         A340-28-5021, dated April 6,
                                          2005.
------------------------------------------------------------------------

    Service Bulletins A330-28-3086 and A340-28-4100, Revision 01, 
include procedures for performing repetitive borescope inspections of 
the right trim tank for detached or damaged float valves, and related 
investigative/corrective actions if necessary. Service Bulletins A330-
28-3087 and A340-28-4101, both Revision 01, include procedures for 
doing those same actions for the left trim tank. If a float valve is 
detached, or the arms are damaged, the related investigative/corrective 
actions include:

     Doing a detailed visual inspection for damage to the trim 
tank structure;
     Repairing structural damage in accordance with the 
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus 
if the damage exceeds the limits specified in the SRM;
     Removing a detached float valve and associated debris from 
the trim tank;
     Replacing the float valve; and
     Reporting all findings to Airbus.
    These service bulletins also provide the option of deactivating an 
affected trim tank until the float valve can be replaced in accordance 
with the operator's maintenance schedule. In addition, for airplanes on 
which some floats are intact, Service Bulletin A340-28-4100, Revision 
01, provides the option of contacting Airbus for the possible issuance 
of an Airbus No Technical Objection (NTO) letter to allow continued 
operation, for a specified number of flight cycles, without 
deactivating the trim tank.
    Service Bulletins A330-28-3088, A340-28-4102, and A340-28-5007 
include procedures for installing a new, improved float valve, P/N 
62015-1, manufactured by Argo-Tech, in the right trim tank. The 
installation procedures include:

[[Page 37298]]

     Removing the existing float valve and bonding leads;
     Removing a detached float valve and associated debris from 
the trim tank, if necessary;
     Repairing structural damage in accordance with the 
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus 
if the damage exceeds the limits specified in the SRM;
     Preparing the airplane structure to accommodate the new 
electrical bonding;
     Installing P/N 62015-1; and
     Performing a bonding test of the float valve.
    Service Bulletin A330-28-3088 also specifies a life limit of 20,000 
flight cycles since first installation for the new Argo-Tech float 
valve, P/N 62015-1. Service Bulletins A330-28-3088 and A340-28-4102 
state that any removed float valve having a certain part number should 
be sent to Argo-Tech. In addition, Service Bulletin A330-28-3088 
identifies Airbus Service Bulletin A330-55-3022, dated November 4, 
1997, as a concurrent service bulletin; and Service Bulletin A340-28-
4102 identifies Airbus Service Bulletin A340-55-4023, dated November 4, 
1997, as a concurrent service bulletin. The concurrent service 
bulletins include procedures for installing Teflon gore joints in the 
front spar panels.
    Service Bulletin A330-28-3088 states that accomplishing the actions 
specified in that service bulletin cancels the inspections specified in 
Service Bulletin A330-28-3086. Service Bulletin A340-28-4102 states 
that accomplishing the actions specified in that service bulletin 
cancels the inspections specified in Service Bulletin A340-28-4100.
    Procedures for installing a new, improved float valve, P/N L87-13-
002, manufactured by Intertechnique, in the left trim tank, are 
included in the following service bulletins: A330-28-3089, Revision 02; 
A340-28-4103, Revision 02; and A340-28-5010. The installation 
procedures include:

     Removing the existing float valve;
     Removing a detached float valve and associated debris from 
the trim tank, if necessary;
     Repairing structural damage in accordance with the 
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus 
for damage that exceeds the limits specified in the SRM;
     Installing P/N L87-13-002; and
     Performing a bonding test of the float valve.
    Service Bulletin A330-28-3089, Revision 02, also specifies a life 
limit of 24,500 flight cycles since first installation for the new 
Intertechnique float valve, P/N L87-13-002. Service Bulletins A330-28-
3089, Revision 02; A340-28-4103, Revision 02; and A340-28-5010 also 
state that removed float valves having a certain part number should be 
sent to Intertechnique. In addition, Service Bulletin A330-28-3089 
identifies Airbus Service Bulletin A330-55-3022 as a concurrent service 
bulletin; and Service Bulletin A340-28-4103 identifies Airbus Service 
Bulletin A340-55-4023 as a concurrent service bulletin.
    Service Bulletin A330-28-3089, Revision 02, states that 
accomplishing the actions in that service bulletin cancels the 
inspections specified in Service Bulletin A330-28-3087. Service 
Bulletin A340-28-4103, Revision 02, states that accomplishing the 
actions in that service bulletin cancels the inspections specified in 
Service Bulletin A340-28-4101.
    Procedures for installing a new, improved float valve, P/N L87-13-
003, manufactured by Intertechnique, in the left trim tank, are 
included in the following service bulletins: A330-28-3094, A340-28-
4111, and A340-28-5021. The installation procedures include:

     Removing the existing float valve;
     Removing a detached float valve and associated debris from 
the trim tank, if necessary;
     Repairing structural damage in accordance with the 
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus 
for damage that exceeds the limits specified in the SRM;
     Installing P/N L87-13-003; and
     Performing a bonding test of the float valve.
    Service Bulletin A330-28-3094 states that, if P/N L87-13-002 has 
not been installed, accomplishing the actions specified in that service 
bulletin eliminates the need for accomplishing the actions specified in 
Service Bulletin A330-28-3089. Service Bulletin A340-28-4111 states 
that, if P/N L87-13-002 has not been installed, accomplishing the 
actions specified in that service bulletin eliminates the need for 
accomplishing the actions specified in Service Bulletin A340-28-4103. 
Service Bulletin A340-28-5021 states that, if P/N L87-13-002 has not 
been installed, accomplishing the actions specified in that service 
bulletin eliminates the need for accomplishing the actions specified in 
Service Bulletin A340-28-5010.
    The DGAC mandated the service information and issued French 
airworthiness directives F-2005-003, dated January 5, 2005, and F-2005-
004 R1 and F-2005-005 R1, both dated April 27, 2005, to ensure the 
continued airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are 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 proposing this AD, which would require repetitive 
borescope inspections of the left and right fuel tanks of the trimmable 
horizontal stabilizers (trim tanks) for detached or damaged float 
valves; related investigative/corrective actions if necessary; and the 
eventual replacement of all float valves in the left and right trim 
tanks with new, improved float valves, which terminates the need for 
the repetitive inspections. This proposed AD would also require 
repetitive replacement of certain new, improved float valves.

Differences Among the Proposed AD, French Airworthiness Directives, and 
Service Information

    All of the service bulletins specify that if the structural damage 
caused by a detached float exceeds the limits in the applicable Airbus 
SRM, you may contact the manufacturer for instructions on how to repair 
the damage. This proposed AD would require you to contact us, or the 
DGAC (or its delegated agent), for instructions on how to repair damage 
that exceeds the limits in the SRM. Also, this proposed AD provides the 
option of either repairing any structural damage in accordance with the 
applicable service bulletin, or in accordance with a method approved by 
us, or the DGAC (or its delegated agent). In light of the type of 
repair that would be required to address the unsafe condition, and 
consistent with existing bilateral airworthiness agreements, we have 
determined that, for this proposed AD, a repair we or the DGAC approve 
would be acceptable for compliance with this proposed AD.
    Service Bulletin A340-28-4100, Revision 01, provides operators the 
option of contacting Airbus for the possible issuance of an Airbus NTO

[[Page 37299]]

letter to allow continued operation without deactivating the trim tank 
for a specified number of flight cycles. This proposed AD would not 
allow that action. We can better ensure long-term continued operational 
safety by having operators correct the source of the problem, the trim 
tank. Anyone may apply for an AMOC and make a request to temporarily 
operate an airplane without a deactivated trim tank.
    Operators should note that, although the Accomplishment 
Instructions of certain referenced service bulletins describe 
procedures for submitting an inspection report sheet to Airbus, or 
returning removed float valves to the float valve manufacturer, this 
proposed AD would not require those actions.

Concurrent Service Information

    Airbus Service Bulletins A330-28-3088 and A330-28-3089 identify 
Airbus Service Bulletin A330-55-3022 as a concurrent service bulletin, 
and Airbus Service Bulletins A340-28-4102 and A340-28-4103 identify 
Airbus Service Bulletin A340-55-4023 as a concurrent service bulletin. 
The concurrent service bulletins include procedures for installing 
Teflon gore joints on front spar access panel 343ER. That action 
reduces the number of work hours needed to remove and install the 
access panel when the new, improved float valves are installed. The 
French airworthiness directives do not mandate accomplishment of the 
concurrent service bulletins and this proposed AD would not require 
accomplishment of the concurrent service bulletins.

Clarification of Life Limit in Paragraph (h) of the Proposed AD

    For Airbus Model A330 series airplanes, French airworthiness 
directive F-2005-003, dated January 5, 2005, mandates a life limit of 
24,500 flight cycles ``since new'' for Intertechnique float valve, P/N 
L87-13-002. This P/N failed in a mode that potentially re-introduced 
the possible ignition source, so a life limit is necessary. The DGAC 
has informed us that it does not intend to issue a parallel French 
airworthiness directive for Airbus Model A340 series airplanes. The 
DGAC states that a float valve life limit of 24,500 flight cycles is 
above the A340 design service goal of 20,000 flight cycles. 
Intertechnique float valve, P/N L87-13-003, did not exhibit any failure 
during qualification tests and does not have a life limit for Airbus 
Model A330 or A340 series airplanes.

Clarification of Inspection Terminology

    In this proposed AD, the ``detailed visual inspection'' specified 
in the Airbus service bulletins is referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in Note 1 of this AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
of Model A330 series airplanes to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                   Number of U.S.-
               Action                      Work hours        Average labor          Parts             Cost per       registered          Fleet cost
                                                             rate per hour                            airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Borescope inspection, per            2 (1 hour per float,              $65  None.................            $130              25  $3,250, per
 inspection cycle.                    2 floats per                                                                                  inspection cycle.
                                      airplane).
Installation of float valves.......  4 (2 per valve, 2                  65  No charge............             260              25  $6,500, per
                                      valves per airplane).                                                                         installation.
Bonding test (new, improved float    1....................              65  None.................              65              25  $1,625.
 valves, left trim tank only).
--------------------------------------------------------------------------------------------------------------------------------------------------------

    Currently, there are no affected Model A340 series airplanes on the 
U.S. Register. However, should an affected airplane be imported and 
placed on the U.S. Register in the future, it would be subject to the 
proposed actions of this AD. The estimated costs would be the same as 
those listed above for the Model A330 series airplanes.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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 proposed AD. 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, Safety.

The Proposed Amendment

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

[[Page 37300]]

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 FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Airbus: Docket No. FAA-2005-21702; Directorate Identifier 2005-NM-
024-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by July 29, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330 and A340 series 
airplanes, certificated in any category, as identified in Table 1 of 
this AD.

                         Table 1.--Applicability
------------------------------------------------------------------------
                                             Except those modified in
              Airbus model                     production by airbus
                                                   modification
------------------------------------------------------------------------
A330 series airplanes..................  51953 and either 52110 or 53081
A340-200 and -300 series airplanes.....  51953 and either 52110 or 53081
A340-541 and -642 airplanes............  51951 and either 52109 or 53081
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD was prompted by reports of detached and damaged 
float valves in the left and right fuel tanks of the trimmable 
horizontal stabilizers (trim tanks). We are issuing this AD to 
prevent, in the event of a lightning strike to the horizontal 
stabilizer, sparking of metal parts and debris from detached and 
damaged float valves, or a buildup of static electricity, which 
could result in ignition of fuel vapors 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.

Borescope Inspection

    (f) At the later of the times specified in paragraph (f)(1) and 
(f)(2) of this AD: Do a borescope inspection for detached or damaged 
float valves in the left and right trim tanks, by doing the 
applicable actions in the Accomplishment Instructions of Airbus 
Service Bulletins A330-28-3086, dated July 24, 2003; and A330-28-
3087, Revision 01, dated August 16, 2004 (for Model A330 series 
airplanes); or A340-28-4100 and A340-28-4101, both Revision 01, both 
dated August 16, 2004 (for Model A340-200 and -300 series 
airplanes); as applicable.
    (1) Prior to the accumulation of 2,500 total flight cycles or 
15,000 total flight hours, whichever is first.
    (2) Within 7,500 flight hours after the effective date of this 
AD.

Related Investigative and Corrective Actions

    (g) Depending on the results of the inspection required by 
paragraph (f) of this AD: Do the applicable actions in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin identified in Table 2 of this AD, at the times specified in 
Table 2.

                    Table 2.--Inspection Results and Related Investigative/Corrective Actions
----------------------------------------------------------------------------------------------------------------
                                                                                       In accordance with Airbus
     If inspection results reveal--                         Then--                        Service Bulletin--
----------------------------------------------------------------------------------------------------------------
Detached or damaged float valve in the    Before further flight: (1) Remove the       A330-28-3086, dated July
 right trim tank.                          detached float and float debris from the    24, 2003.
                                           trim tank and do a detailed inspection     A340-28-4100, Revision 01,
                                           for structural damage to the affected       dated August 16, 2004.
                                           trim tank tank. Repair any structural
                                           damage to the trim tank or deactivate the
                                           trim tank, before further flight, in
                                           accordance with the applicable service
                                           bulletin, or in accordance with a method
                                           approved by the Manager, International
                                           Branch, ANM-116, FAA, Transport Airplane
                                           Directorate; or the Direction
                                           G[eacute]n[eacute]rale de l'Aviation
                                           Civile (DGAC) (or its delegated agent).
                                           Where the service bulletin specifies to
                                           contact the manufacturer, instead contact
                                           the Manager, International Branch, ANM-
                                           116, or the DGAC (or its delegated agent).
                                          Before further flight, after doing the      A330-28-3086, dated July
                                           detailed inspection and repairing any       24, 2003.
                                           structural damage: (2) Replace the         A330-28-3088, dated April
                                           affected float valve with a new unit        27, 2004.
                                           having the same part number (P/N), or a    A340-28-4100, Revision 01,
                                           new, improved float valve, P/N 62015-1.     dated August 16, 2004.
                                           If a new unit of P/N 61600 is installed,   A340-28-4102, dated April
                                           thereafter, do the inspection required by   27, 2004.
                                           paragraph (f) of this AD at intervals not
                                           to exceed 2,500 flight cycles or 15,000
                                           flight hours, whichever is first, after
                                           the most recent inspection, until
                                           paragraph (h) of this AD is accomplished.
Detached or damaged float valve in the    Before further flight: (1) Remove the       A330-28-3087, Revision 01,
 left trim tank.                           detached float and float debris from the    dated August 16, 2004.
                                           trim tank and do a detailed inspection     A340-28-4101, Revision 01,
                                           for structural damage to the affected       dated August 16, 2004.
                                           trim tank. Repair any structural damage
                                           to the trim tank or deactivate the trim
                                           tank, before further flight, in
                                           accordance with the applicable service
                                           bulletin, or in accordance with a method
                                           approved by the Manager, International
                                           Branch, ANM-116, FAA, Transport Airplane
                                           Directorate; or the DGAC (or its
                                           delegated agent). Where the service
                                           bulletin specifies to contact the
                                           manufacturer, instead contact the
                                           Manager, International Branch, ANM-116,
                                           or the DGAC (or its delegated agent).

[[Page 37301]]

 
                                          Before further flight, after doing the      A330-28-3087, Revision 01,
                                           detailed inspection and repairing any       dated August 16, 2004.
                                           structural damage: (2) Replace the         A330-28-3089, Revision 02,
                                           affected float valve with either a new      dated April 1, 2005.
                                           unit having that same P/N, or a new        A330-28-3094, dated April
                                           improved float valve, P/N L87-13-002 or P/  7, 2005.
                                           N L87-13-003. If a new unit of P/N L87-13- A340-28-4101, Revision 01,
                                           001 is installed, thereafter, do the        dated August 16, 2004.
                                           inspection required by paragraph (f) of    A340-28-4103, Revision 02,
                                           this AD at intervals not to exceed 2,500    dated April 1, 2005.
                                           flight cycles or 15,000 flight hours,      A340-28-4111, dated April
                                           whichever is first, after the most recent   6, 2005.
                                           inspection, until paragraph (h) of this
                                           AD is accomplished. For Airbus Model A330
                                           series airplanes, if a float valve having
                                           P/N L87-13-002 is installed, thereafter,
                                           replace that float valve with a float
                                           valve having that same P/N at intervals
                                           not to exceed those specified in
                                           paragraph (h) of this AD. Installation of
                                           P/N L87-13-003 on Airbus Model A330
                                           series airplanes terminates the
                                           repetitive float valve replacement
                                           required by paragraph (h) of this AD.
No damaged or detached float valve in     Within 10,000 flight hours or 1,500 flight  A330-28-3086, dated July
 the right trim tank.                      cycles, whichever is first, from the        24, 2003.
                                           initial float inspection done in           A330-28-3088, dated April
                                           accordance with paragraph (f) of this AD,   27, 2004.
                                           replace the existing Argo-new Tech float   A340-28-4100, Revision 01,
                                           valve, P/N 61600, with either a unit        dated August 16, 2004.
                                           having that same P/N, or a new, improved   A340-28-4102, dated April
                                           float valve, P/N 62015-1. If a new unit     27, 2004.
                                           of P/N 61600 is installed, thereafter,
                                           repeat the inspection required by
                                           paragraph (f) of this AD at intervals not
                                           to exceed 2,500 flight cycles or 15,000
                                           flight hours, whichever is first, until
                                           paragraph (h) of this AD is accomplished.
No damaged detached float valve in the    Within 10,000 flight hours or 1,500 flight  A330-28-3087, Revision 01,
 left trim tank.                           cycles, whichever is first, from the        August 16, 2004.
                                           initial inspection done in accordance      A330-28-3089, Revision 02,
                                           with paragraph (f) of this AD, replace      dated April 1, 2005.
                                           the existing trim tank Intertechnique      A330-28-3094, dated April
                                           float valve, P/N L87-13-001, with either    7, 2005.
                                           a new unit having that same P/N, or a new  A340-28-4101, Revision 01,
                                           improved float valve, P/N L87-13-002 or P/  dated August 16, 2004.
                                           N L87-13-003. If a new unit of P/N L87-13- A340-28-4103, Revision 02,
                                           001 is installed, thereafter, do the        dated April 1, 2005.
                                           inspection required by paragraph (f) of    A340-28-4111, dated April
                                           this AD at intervals not to exceed 2,500    6, 2005.
                                           flight cycles or 15,000 flight hours,
                                           whichever is first, after the most recent
                                           inspection, until paragraph (h) of this
                                           AD is accomplished. For Airbus Model A330
                                           series airplanes, if a float valve having
                                           P/N L87-13-002 is installed, thereafter,
                                           replace that float valve with a float
                                           valve having that same P/N at intervals
                                           not to exceed those specified in
                                           paragraph (h) of this AD. Installation of
                                           P/N L87-13-003 on Airbus Model A330
                                           series airplanes terminates the
                                           repetitive float valve replacement
                                           required by paragraph (h) of this AD.
----------------------------------------------------------------------------------------------------------------


    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.''

Installation of New, Improved Float Valves

    (h) Within 50 months after the effective date of this AD: 
Replace any Argo-Tech float valve, P/N 61600, with a new, improved 
float valve, P/N 62015-1; replace any Intertechnique float valve, P/
N L87-13-001, with a new, improved float valve, P/N L87-13-002 or P/
N L87-13-003; and do any applicable corrective action; by 
accomplishing the actions specified in the Accomplishments 
Instructions of the applicable service bulletin in Table 3 of this 
AD. Do any applicable corrective action before further flight. For 
Airbus Model A330 series airplanes, if P/N L87-13-002 is installed, 
replace the float valve thereafter at intervals not to exceed 24,500 
flight cycles. Installation of P/N L87-13-003 on Airbus Model A330 
series airplanes terminates the repetitive float valve replacement 
required by this paragraph. Installation of either P/N L87-13-002 or 
P/N L87-13-003 terminates the borescope inspections required by 
paragraphs (f) and (g) of this AD. Where the service bulletin 
specifies to contact the manufacturer, instead contact the Manager, 
International Branch, ANM-116, or the DGAC (or its delegated agent).

           Table 3.--Service Information for New Float Valves
------------------------------------------------------------------------
                                                       Airbus service
         Airbus model            Float valve P/N          bulletin
------------------------------------------------------------------------
A330 series airplanes.........  62015-1..........  A330-28-3088, dated
                                L87-13-002.......   April 27, 2004.
                                L87-13-003.......  A330-28-3089,
                                                    Revision 02, dated
                                                    April 1, 2005.
                                                   A330-28-3094, dated
                                                    April 7, 2005.
340-200 and -300 series         62015-1..........  A340-28-4102, dated
 airplanes.                     L87-13-002.......   April 27, 2004.
                                L87-13-003.......  A340-28-4103,
                                                    Revision 02, dated
                                                    April 1, 2005.
                                                   A340-28-4111, dated
                                                    April 6, 2005.
A340-541 and -642 airplanes...  62015-1..........  A340-28-5007, dated
                                L87-13-002.......   May 7, 2004.
                                L87-13-003.......  A340-28-5010, dated
                                                    May 7, 2004.
                                                   A340-28-5021, dated
                                                    April 6, 2005.
------------------------------------------------------------------------


[[Page 37302]]

Actions Accomplished Previously

    (i) Inspections and related investigative and corrective actions 
accomplished before the effective date of this AD, in accordance 
with any applicable Airbus service bulletin identified in Table 4 of 
this AD, are acceptable for compliance with the corresponding 
actions specified in this AD.

    Table 4.--Service Information For Actions Accomplished Previously
------------------------------------------------------------------------
              Airbus model                   Airbus service bulletin
------------------------------------------------------------------------
A330 series airplanes..................  A330-28-3087, dated July 24,
                                          2003.
                                         A330-28-3089, Revision 01,
                                          dated May 12, 2004.
A340-200 and -300 series airplanes.....  A340-28-4100, dated July 24,
                                          2003.
                                         A340-28-5010, dated May 7,
                                          2004.
                                         A340-28-5021, dated April 6,
                                          2005.
------------------------------------------------------------------------

No Submission of Information/Parts

    (j) Where any Airbus service bulletin specifies to submit 
information to Airbus, or send removed float valves to either Argo-
Tech or Intertechnique, those actions are not required by this AD.

Alternative Methods of Compliance (AMOCs)

    (k) The Manager, International Branch, 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.

Related Information

    (l) French airworthiness directives F-2005-003, dated January 5, 
2005, and F-2005-004 R1 and F-2005-005 R1, both dated April 27, 
2005, also address the subject of this AD.

    Issued in Renton, Washington, on June 22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-12839 Filed 6-28-05; 8:45 am]
BILLING CODE 4910-13-P