Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, A340-200 and -300 Series Airplanes, and A340-541 and -642 Airplanes, 5971-5976 [06-989]

Download as PDF Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations crack using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Optional Preventive Modification (h) Installing an external doubler on a corner in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002, terminates the repetitive inspection intervals of paragraph (f) of this AD for that corner. Before the accumulation of 17,000 flight cycles after the installation: Do the next inspection of that corner, as specified in paragraph (f) of this AD. Repeat the inspections in paragraph (f) of this AD for that corner thereafter at intervals not to exceed 4,400 flight cycles. No Reporting Required (i) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Actions Accomplished In Accordance With Previous Issue of Service Bulletin (j) Actions accomplished before the effective date of this AD in accordance with McDonnell Douglas Service Bulletin C8–53– 079, dated January 31, 2001, are acceptable for compliance with the corresponding action in this AD. wwhite on PROD1PC65 with RULES Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (4) Inspections required by this AD of specified areas of Principal Structural Element (PSE) 53.08.044 are acceptable for compliance with the applicable requirements of paragraphs (a) and (b) of AD 93–01–15, amendment 39–8469 (58 FR 5576, January 22, 1993). The remaining areas of the affected PSEs must be inspected and repaired as applicable, in accordance with AD 93–01–15. Material Incorporated by Reference (l) You must use Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance VerDate Aug<31>2005 16:29 Feb 03, 2006 Jkt 208001 with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at https:// dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on January 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–987 Filed 2–3–06; 8:45 am] BILLING CODE 4910–13–P 5971 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. This AD becomes effective March 13, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 13, 2006. DATES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. ADDRESSES: 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. FOR FURTHER INFORMATION CONTACT: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21702; Directorate Identifier 2005–NM–024–AD; Amendment 39–14473; AD 2006–03–09] SUPPLEMENTARY INFORMATION: RIN 2120–AA64 You may examine the airworthiness directive (AD) docket on the Internet at https://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 street address stated in the ADDRESSES section. Airworthiness Directives; Airbus Model A330–200 and –300 Series Airplanes, A340–200 and –300 Series Airplanes, and A340–541 and –642 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300 series airplanes, A340–200 and –300 series airplanes, and A340–541 and –642 airplanes. This AD requires 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 AD also requires repetitive replacement of certain new, improved float valves. This AD results from reports of detached and damaged float valves in the trim tanks. We are issuing this AD to prevent, in the event of a lightning strike to the horizontal PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Examining the Docket Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A330 and A340 series airplanes. That NPRM was published in the Federal Register on June 29, 2005 (70 FR 37296). That NPRM proposed to 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. That NPRM also proposed to require repetitive replacement of certain new, improved float valves. E:\FR\FM\06FER1.SGM 06FER1 5972 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations Requests That Did Not Result in a Change to the NPRM Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Requests That Resulted in a Change to the NPRM wwhite on PROD1PC65 with RULES Request To Add Another Service Bulletin One commenter requests that the NPRM reference an additional service bulletin. The commenter explains that Airbus Service Bulletin A330–28–3093, dated June 16, 2005, installs the same Airbus modification number (53081) as Airbus Service Bulletin A330–28–3094, dated April 7, 2005, which was referenced in the NPRM as an appropriate source of service information. The commenter explains that the effectivity in Airbus Service Bulletin A330–28–3093 includes all of the commenter’s airplanes, while Airbus Service Bulletin A330–28–3094 does not. We agree to add Airbus Service Bulletin A330–28–3093 as another method of compliance to the requirements of the AD. We note that adding this service bulletin is for the convenience of the operator in accomplishing the actions required by this AD, and does not add or remove any airplane listed in the applicability of this AD. Request To Revise the Costs of Compliance The same commenter requests that the NPRM be revised to add an estimated cost for access to each of the valves during replacement of the valves, which is a terminating action. The commenter notes that the service information estimates a total of 76 hours of access related labor time. The commenter estimates a more realistic value to be 116 hours. The commenter recognizes that access time is typically not included in the labor estimates of ADs. However, the commenter advises that there are no tasks in the A330 maintenance program that require access to this area. Therefore, the access hours will be driven solely and specifically by the NPRM. We agree that, in this case, it is appropriate to consider the time necessary for access. We also recognize that different operators may have different access times based on different airplane configurations or other considerations. The estimated cost information for access that is provided by the manufacturer is the latest information that we have, and we have revised the AD to reflect that estimate. VerDate Aug<31>2005 16:29 Feb 03, 2006 Jkt 208001 Request To Address Defective Parts Manufacturer Approval (PMA) Parts One commenter requests that the NPRM be modified to include possible ‘‘defective’’ parts manufactured with a parts manufacturer approval (PMA) that may be installed in lieu of the defective original equipment manufacturer (OEM) part specified in the NPRM. The commenter states that a ‘‘known’’ PMA part exists for the defective OEM part specified in the NPRM, and may contain the same defects as the specified OEM part. The commenter further points out that, if a PMA part is defective and currently installed, the NPRM would not require its removal. We concur with the commenter’s general request that, if we know that an unsafe condition also exists in PMA parts, the AD should address those parts, as well as the original parts. Contrary to the commenter’s assertion that the known PMA part is not covered by the wording of the NPRM, the ‘‘known’’ PMA part identified by the commenter does have the same part number as the part number specified in the NPRM. Therefore, it is also subject to the requirements of this AD. We are not aware of other PMA parts that may have a different part number. The commenter’s remarks are timely in that the Transport Airplane Directorate currently is in the process of reviewing this issue as it applies to transport category airplanes. We acknowledge that there may be other ways of addressing this issue to ensure that unsafe PMA parts are identified and addressed. Once we have thoroughly examined all aspects of this issue, including input from industry, and have made a final determination, we will consider whether our policy regarding addressing PMA parts in ADs needs to be revised. We consider that to delay this AD action would be inappropriate, since we have determined that an unsafe condition exists and that replacement of certain parts must be accomplished to ensure continued safety. Therefore, no change has been made to the final rule in this regard. Request to Reference PMA Parts The same commenter also requests that the language in the NPRM be changed to permit installation of PMA equivalent parts. The commenter states that the mandated installation of a certain part number in the NPRM ‘‘is at variance with the higher authority of 14 CFR Section 21.303.’’ We infer that the commenter would like the AD to permit installation of any PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 equivalent PMA parts so that it is not necessary for an operator to request approval of an alternative method of compliance (AMOC) in order to install an ‘‘equivalent’’ PMA part. Whether an alternative part is ‘‘equivalent’’ in adequately resolving the unsafe condition can only be determined on a case-by-case basis based on a complete understanding of the unsafe condition. We are not currently aware of any such parts. Our policy is that, in order for operators to replace a part with one that is not specified in the AD, they must request an AMOC. This is necessary so that we can make a specific determination that an alternative part is or is not susceptible to the same unsafe condition. In response to the commenter’s statement regarding a ‘‘variance with FAR 21.303,’’ under which the FAA issues PMAs, this statement appears to reflect a misunderstanding of the relationship between ADs and the certification procedural regulations of part 21 of the FARs (14 CFR part 21). Those regulations, including section 21.303 of the FARs (14 CFR part 21.303), are intended to ensure that aeronautical products comply with the applicable airworthiness standards. But ADs are issued when, notwithstanding those procedures, we become aware of unsafe conditions in these products or parts. Therefore, an AD takes precedence over design approvals when we identify an unsafe condition, and mandating installation of a certain part number in an AD is not at variance with section § 21.303. The AD provides a means of compliance for operators to ensure that the identified unsafe condition is addressed appropriately. For an unsafe condition attributable to a part, the AD normally identifies the replacement parts necessary to obtain that compliance. As stated in section 39.7 of the FARs (14 CFR 39.7), ‘‘Anyone who operates a product that does not meet the requirements of an applicable airworthiness directive is in violation of this section.’’ Unless an operator obtains approval for an AMOC, replacing a part with one not specified by the AD would make the operator subject to an enforcement action and result in a civil penalty. No change to the AD is necessary in this regard. Editorial Changes to the AD Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any E:\FR\FM\06FER1.SGM 06FER1 5973 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations approved AMOC on any airplane to which the AMOC applies. economic burden on any operator nor increase the scope of the AD. Conclusion Explanation of Change to Applicability We have revised the applicability of the existing AD to identify model designations as published in the most recent type certificate data sheet for the affected models. We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the Costs of Compliance The following table provides the estimated costs, at an average labor rate per hour of $65, for U.S. operators of Model A330–200 and –300 series airplanes to comply with this AD. ESTIMATED COSTS Number of U.S. registered airplanes Cost per airplane Action Work hours Parts Repetitive borescope inspection, per inspection cycle. Installation of float valves (including access). Bonding test (new, improved float valves, left trim tank only). 2 hours for inspection ....................... None ........ $130 25 4 hours (2 per valve, 2 valves per airplane) plus 76 hours for access. 1 ........................................................ No charge 5,200 25 65 25 Currently, there are no affected Model A340–200 and –300 series airplanes and A340–541 and –642 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 actions of this AD. The estimated costs would be the same as those listed above for the Model A330–200 and –300 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. None ........ Fleet cost $3,250, per inspection cycle. $130,000, per installation. $1,625. Regulatory Findings Adoption of the Amendment We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. I List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–03–09 Airbus: Amendment 39– 14473. Docket No. FAA–2005–21702; Directorate Identifier 2005–NM–024–AD. Effective Date (a) This AD becomes effective March 13, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330– 201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes; and A340–211, –212, –213 –311, –312, –313, –541, and –642 airplanes; certificated in any category, as identified in Table 1 of this AD. TABLE 1.—APPLICABILITY wwhite on PROD1PC65 with RULES Airbus model Except those modified in production by Airbus modification A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes. A340–211, –212, –213, –311, –312, –313 airplanes ............................... A340–541 and –642 airplanes ................................................................. VerDate Aug<31>2005 16:29 Feb 03, 2006 Jkt 208001 PO 00000 Frm 00005 Fmt 4700 51953 and either 52110 or 53081. 51953 and either 52110 or 53081. 51951 and either 52109 or 53081. Sfmt 4700 E:\FR\FM\06FER1.SGM 06FER1 5974 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 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 A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes); or A340–28–4100 and A340–28–4101, both Revision 01, both dated August 16, 2004 (for Model A340–211, –212, –213, –311, –312, and –313 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 trim tank and do a detailed tank 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 Di´ ´ rection 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, in accordance with the applicable service bulletin. 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. wwhite on PROD1PC65 with RULES No damaged or detached float valve in the left trim tank. VerDate Aug<31>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).. 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 A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 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 A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes terminates the repetitive float valve replacement required by paragraph (h) of this AD.. 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 Argo-Tech float valve, P/N 61600, with either a new 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.. 16:29 Feb 03, 2006 Jkt 208001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\06FER1.SGM 06FER1 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. A330–28–3087, Revision 01, dated August 16, 2004. A330–28–3089, Revision 02, dated April 1, 2005. A330–28–3093, dated June 16, 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. Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 5975 TABLE 2.—INSPECTION RESULTS AND RELATED INVESTIGATIVE/CORRECTIVE ACTIONS—Continued If inspection results reveal— No damaged or detached float valve in the left trim tank. Then— In accordance with Airbus service bulletin— 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 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 A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 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 A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 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. A330–28–3093, dated June 16, 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. 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– 201, –202, –203, –223, —243, –301, –321, –322, –323, –341, –342, and –343 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 A330–201, –202, –203, –223, —243, –301, –321, –322, –323, –341, –342, and –343 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 A330–201, –202, –203, –223, —243, –301, –321, –322, –323, –341, –342, and –343 airplanes. 62015–1 .. L87–13– 002. L87–13– 003. L87–13– 003. 62015–1 .. L87–13– 002. L87–13– 003. 62015–1 .. L87–13– 002. L87–13– 003. A340–211, –212, –213, –311, –312, and —313 airplanes. A340–541— and –642 airplanes. Airbus service bulletin A330–28–3088, A330–28–3089, A330–28–3093, A330–28–3094, A340–28–4102, dated April 27, 2004. A340–28–4103, Revision 02, dated April 1, 2005. A340–28–4111, dated April 6, 2005. A340–28–5007, dated May 7, 2004. A340–28–5010, dated may 7, 2004. A340–28–5021, dated April 6, 2005. wwhite on PROD1PC65 with RULES Actions Accomplished Previously (i) Inspections and related investigative and corrective actions accomplished before VerDate Aug<31>2005 16:29 Feb 03, 2006 Jkt 208001 dated April 27, 2004. Revision 02, dated April 1, 2005. dated June 16, 2005. dated April 7, 2005. the effective date of this AD, in accordance with any applicable Airbus service bulletin identified in Table 4 of this AD, are PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 acceptable for compliance with the corresponding actions specified in this AD. E:\FR\FM\06FER1.SGM 06FER1 5976 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations TABLE 4.—SERVICE INFORMATION FOR ACTIONS ACCOMPLISHED PREVIOUSLY Airbus model Airbus service bulletin A330–201, –202, –203, –223, —243, –301, –321, –322, –323, –341, –342, and –343 airplanes. A340–211, –212, –213, –311, –312, and —313 airplanes. 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)(1) 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. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify A330–28–3087, dated July 24, 2003. A330–28–3089, Revision 01, dated May 12, 2004. A340–28–4100, A340–28–4101, A340–28–4103, A340–28–5010, A340–28–5021, dated July 24, 2003. dated July 24, 2003. Revision 01, dated May 12, 2004. dated May 7, 2004. dated April 6, 2005. the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. 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. Material Incorporated by Reference (m) You must use the documents specified in Table 5 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. TABLE 5.—MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin Revision level A330–28–3086, excluding Appendix 01 ........................................................................... A330–28–3087, excluding Appendix 01 ........................................................................... A330–28–3088 ................................................................................................................. A330–28–3089 ................................................................................................................. A330–28–3093 ................................................................................................................. A330–28–3094 ................................................................................................................. A340–28–4100 ................................................................................................................. A340–28–4101, excluding Appendix 01 ........................................................................... A340–28–4102 ................................................................................................................. A340–28–4103 ................................................................................................................. A340–28–4111 ................................................................................................................. A340–28–5007 ................................................................................................................. A340–28–5010 ................................................................................................................. A340–28–5021 ................................................................................................................. Original .... 01 ............. Original .... 02 ............ Original .... Original .... 01 ............ 01 ............. Original .... 02 ............ Original .... Original .... Original .... Original .... Issued in Renton, Washington, on January 27, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–989 Filed 2–3–06; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 airplanes, and EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. This AD requires inspecting the pilot’s and copilot’s seat tracks for proper locking of the seats, and adjusting or replacing the seat tracks if necessary. This AD also requires replacement of the seat locking pin on certain SICMA-brand seats. The actions specified by this AD are intended to prevent uncommanded movement of the pilot’s or co-pilot’s seat, which could interfere with the 14 CFR Part 39 [Docket No. 2003–NM–271–AD; Amendment 39–14470; AD 2006–03–06] wwhite on PROD1PC65 with RULES Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: Jkt 208001 Final rule. ACTION: Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 Airplanes and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP Airplanes 16:29 Feb 03, 2006 July 24, 2003. August 16, 2004. April 27, 2004. April 1, 2005. June 16, 2005. April 7, 2005. August 16, 2004. August 16, 2004. April 27, 2004. April 1, 2005. April 6, 2005. May 7, 2004. May 7, 2004. April 6, 2005. DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 VerDate Aug<31>2005 Date PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\06FER1.SGM 06FER1

Agencies

[Federal Register Volume 71, Number 24 (Monday, February 6, 2006)]
[Rules and Regulations]
[Pages 5971-5976]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-989]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21702; Directorate Identifier 2005-NM-024-AD;
Amendment 39-14473; AD 2006-03-09]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-200 and -300 Series
Airplanes, A340-200 and -300 Series Airplanes, and A340-541 and -642
Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A330-200 and -300 series airplanes, A340-200 and -
300 series airplanes, and A340-541 and -642 airplanes. This AD requires
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 AD also requires
repetitive replacement of certain new, improved float valves. This AD
results from reports of detached and damaged float valves in the 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.

DATES: This AD becomes effective March 13, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 13,
2006.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this 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:

Examining the Docket

You may examine the airworthiness directive (AD) docket on the
Internet at https://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 street address stated in the ADDRESSES section.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Airbus Model
A330 and A340 series airplanes. That NPRM was published in the Federal
Register on June 29, 2005 (70 FR 37296). That NPRM proposed to 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. That NPRM also proposed to
require repetitive replacement of certain new, improved float valves.

[[Page 5972]]

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.

Requests That Resulted in a Change to the NPRM

Request To Add Another Service Bulletin

One commenter requests that the NPRM reference an additional
service bulletin. The commenter explains that Airbus Service Bulletin
A330-28-3093, dated June 16, 2005, installs the same Airbus
modification number (53081) as Airbus Service Bulletin A330-28-3094,
dated April 7, 2005, which was referenced in the NPRM as an appropriate
source of service information. The commenter explains that the
effectivity in Airbus Service Bulletin A330-28-3093 includes all of the
commenter's airplanes, while Airbus Service Bulletin A330-28-3094 does
not.
We agree to add Airbus Service Bulletin A330-28-3093 as another
method of compliance to the requirements of the AD. We note that adding
this service bulletin is for the convenience of the operator in
accomplishing the actions required by this AD, and does not add or
remove any airplane listed in the applicability of this AD.

Request To Revise the Costs of Compliance

The same commenter requests that the NPRM be revised to add an
estimated cost for access to each of the valves during replacement of
the valves, which is a terminating action. The commenter notes that the
service information estimates a total of 76 hours of access related
labor time. The commenter estimates a more realistic value to be 116
hours. The commenter recognizes that access time is typically not
included in the labor estimates of ADs. However, the commenter advises
that there are no tasks in the A330 maintenance program that require
access to this area. Therefore, the access hours will be driven solely
and specifically by the NPRM.
We agree that, in this case, it is appropriate to consider the time
necessary for access. We also recognize that different operators may
have different access times based on different airplane configurations
or other considerations. The estimated cost information for access that
is provided by the manufacturer is the latest information that we have,
and we have revised the AD to reflect that estimate.

Requests That Did Not Result in a Change to the NPRM

Request To Address Defective Parts Manufacturer Approval (PMA) Parts

One commenter requests that the NPRM be modified to include
possible ``defective'' parts manufactured with a parts manufacturer
approval (PMA) that may be installed in lieu of the defective original
equipment manufacturer (OEM) part specified in the NPRM. The commenter
states that a ``known'' PMA part exists for the defective OEM part
specified in the NPRM, and may contain the same defects as the
specified OEM part. The commenter further points out that, if a PMA
part is defective and currently installed, the NPRM would not require
its removal.
We concur with the commenter's general request that, if we know
that an unsafe condition also exists in PMA parts, the AD should
address those parts, as well as the original parts. Contrary to the
commenter's assertion that the known PMA part is not covered by the
wording of the NPRM, the ``known'' PMA part identified by the commenter
does have the same part number as the part number specified in the
NPRM. Therefore, it is also subject to the requirements of this AD. We
are not aware of other PMA parts that may have a different part number.
The commenter's remarks are timely in that the Transport Airplane
Directorate currently is in the process of reviewing this issue as it
applies to transport category airplanes. We acknowledge that there may
be other ways of addressing this issue to ensure that unsafe PMA parts
are identified and addressed. Once we have thoroughly examined all
aspects of this issue, including input from industry, and have made a
final determination, we will consider whether our policy regarding
addressing PMA parts in ADs needs to be revised. We consider that to
delay this AD action would be inappropriate, since we have determined
that an unsafe condition exists and that replacement of certain parts
must be accomplished to ensure continued safety. Therefore, no change
has been made to the final rule in this regard.

Request to Reference PMA Parts

The same commenter also requests that the language in the NPRM be
changed to permit installation of PMA equivalent parts. The commenter
states that the mandated installation of a certain part number in the
NPRM ``is at variance with the higher authority of 14 CFR Section
21.303.''
We infer that the commenter would like the AD to permit
installation of any equivalent PMA parts so that it is not necessary
for an operator to request approval of an alternative method of
compliance (AMOC) in order to install an ``equivalent'' PMA part.
Whether an alternative part is ``equivalent'' in adequately resolving
the unsafe condition can only be determined on a case-by-case basis
based on a complete understanding of the unsafe condition. We are not
currently aware of any such parts. Our policy is that, in order for
operators to replace a part with one that is not specified in the AD,
they must request an AMOC. This is necessary so that we can make a
specific determination that an alternative part is or is not
susceptible to the same unsafe condition.
In response to the commenter's statement regarding a ``variance
with FAR 21.303,'' under which the FAA issues PMAs, this statement
appears to reflect a misunderstanding of the relationship between ADs
and the certification procedural regulations of part 21 of the FARs (14
CFR part 21). Those regulations, including section 21.303 of the FARs
(14 CFR part 21.303), are intended to ensure that aeronautical products
comply with the applicable airworthiness standards. But ADs are issued
when, notwithstanding those procedures, we become aware of unsafe
conditions in these products or parts. Therefore, an AD takes
precedence over design approvals when we identify an unsafe condition,
and mandating installation of a certain part number in an AD is not at
variance with section Sec. 21.303.
The AD provides a means of compliance for operators to ensure that
the identified unsafe condition is addressed appropriately. For an
unsafe condition attributable to a part, the AD normally identifies the
replacement parts necessary to obtain that compliance. As stated in
section 39.7 of the FARs (14 CFR 39.7), ``Anyone who operates a product
that does not meet the requirements of an applicable airworthiness
directive is in violation of this section.'' Unless an operator obtains
approval for an AMOC, replacing a part with one not specified by the AD
would make the operator subject to an enforcement action and result in
a civil penalty. No change to the AD is necessary in this regard.

Editorial Changes to the AD

Clarification of Alternative Method of Compliance (AMOC) Paragraph

We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any

[[Page 5973]]

approved AMOC on any airplane to which the AMOC applies.

Explanation of Change to Applicability

We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.

Conclusion

We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

The following table provides the estimated costs, at an average
labor rate per hour of $65, for U.S. operators of Model A330-200 and -
300 series airplanes to comply with this AD.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Cost per U.S.
Action Work hours Parts airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Repetitive borescope 2 hours for None........... $130 25 $3,250, per
inspection, per inspection inspection. inspection
cycle. cycle.
Installation of float valves 4 hours (2 per No charge...... 5,200 25 $130,000, per
(including access). valve, 2 valves installation.
per airplane)
plus 76 hours
for access.
Bonding test (new, improved 1................ None........... 65 25 $1,625.
float valves, left trim tank
only).
----------------------------------------------------------------------------------------------------------------

Currently, there are no affected Model A340-200 and -300 series
airplanes and A340-541 and -642 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 actions of this AD.
The estimated costs would be the same as those listed above for the
Model A330-200 and -300 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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

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

2006-03-09 Airbus: Amendment 39-14473. Docket No. FAA-2005-21702;
Directorate Identifier 2005-NM-024-AD.

Effective Date

(a) This AD becomes effective March 13, 2006.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A330-201, -202, -203, -223,
-243, -301, -321, -322, -323, -341, -342, and -343 airplanes; and
A340-211, -212, -213 -311, -312, -313, -541, and -642 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
------------------------------------------------------------------------
A330-201, -202, -203, -223, -243, -301, 51953 and either 52110 or
-321, -322, -323, -341, -342, and -343 53081.
airplanes.
A340-211, -212, -213, -311, -312, -313 51953 and either 52110 or
airplanes. 53081.
A340-541 and -642 airplanes............ 51951 and either 52109 or
53081.
------------------------------------------------------------------------

[[Page 5974]]

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 A330-201, -202,
-203, -223, -243, -301, -321, -322, -323, -341, -342, and -343
airplanes); or A340-28-4100 and A340-28-4101, both Revision 01, both
dated August 16, 2004 (for Model A340-211, -212, -213, -311, -312,
and -313 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
If inspection results reveal-- Then-- Airbus service
bulletin--
----------------------------------------------------------------------------------------------------------------
Detached or damaged float valve in Before further flight: (1) Remove the detached A330-28-3086, dated
the right trim tank. float and float debris from trim tank and do a July 24, 2003.
detailed tank inspection for structural damage A340-28-4100, Revision
to the affected trim tank. Repair any 01, dated August 16,
structural damage to the trim tank or 2004.
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 detailed A330-28-3086, dated
inspection and repairing any structural damage: July 24, 2003.
(2) Replace the affected float valve with a new A330-28-3088, dated
unit having the same part number (P/N), or a April 27, 2004.
new, improved float valve, P/N 62015-1, in A340-28-4100, Revision
accordance with the applicable service 01, dated August 16,
bulletin. If a new unit of P/N 61600 is 2004.
installed, thereafter, do the inspection A340-28-4102, dated
required by paragraph (f) of this AD at April 27, 2004.
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 Before further flight: (1) Remove the detached A330-28-3087, Revision
the left trim tank. float and float debris from the trim tank and 01, dated August 16,
do a detailed inspection for structural damage 2004.
to the affected trim tank. Repair any A340-28-4101, Revision
structural damage to the trim tank or 01, dated August 16,
deactivate the trim tank, before further 2004.
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)..
Before further flight, after doing the detailed A330-28-3087, Revision
inspection and repairing any structural damage: 01, dated August 16,
(2) Replace the affected float valve with 2004.
either a new unit having that same P/N, or a A330-28-3089, Revision
new improved float valve, P/N L87-13-002 or P/N 02, dated April 1,
L87-13-003. If a new unit of P/N L87-13-001 is 2005.
installed, thereafter, do the inspection A330-28-3093, dated
required by paragraph (f) of this AD at June 16, 2005.
intervals not to exceed 2,500 flight cycles or A330-28-3094, dated
15,000 flight hours, whichever is first, after April 7, 2005.
the most recent inspection, until paragraph (h) A340-28-4101, Revision
of this AD is accomplished. For Airbus Model 01, dated August 16,
A330-201, -202, -203, -223, -243, -301, -321, - 2004.
322, -323, -341, -342, and -343 airplanes: If a A340-28-4103, Revision
float valve having P/N L87-13-002 is installed, 02, dated April 1,
thereafter, replace that float valve with a 2005.
float valve having that same P/N at intervals A340-28-4111, dated
not to exceed those specified in paragraph (h) April 6, 2005.
of this AD. Installation of P/N L87-13-003 on
Airbus Model A330-201, -202, -203, -223, -243, -
301, -321, -322, -323, -341, -342, and -343
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
the left trim tank. cycles, whichever is first, from the initial July 24, 2003.
inspection done in accordance with paragraph A330-28-3088, dated
(f) of this AD, replace the existing Argo-Tech April 27, 2004.
float valve, P/N 61600, with either a new unit A340-28-4100, Revision
having that same P/N, or a new, improved float 01, dated August 16,
valve, P/N 62015-1. If a new unit of P/N 61600 2004.
is installed, thereafter, repeat the inspection A340-28-4102, dated
required by paragraph (f) of this AD at April 27, 2004.
intervals not to exceed 2,500 flight cycles or
15,000 flight hours, whichever is first, until
paragraph (h) of this AD is accomplished..

[[Page 5975]]

No damaged or detached float valve in Within 10,000 flight hours or 1,500 flight A330-28-3087, Revision
the left trim tank. cycles, whichever is first, from the initial 01, dated August 16,
inspection done in accordance with paragraph 2004.
(f) of this AD, replace the existing A330-28-3089, Revision
Intertechnique float valve, P/N L87-13-001, 02, dated April 1,
with either a new unit having that same P/N, or 2005.
a new improved float valve, P/N L87-13-002 or P/ A330-28-3093, dated
N L87-13-003. If a new unit of P/N L87-13-001 June 16, 2005.
is installed, thereafter, do the inspection A330-28-3094, dated
required by paragraph (f) of this AD at April 7, 2005.
intervals not to exceed 2,500 flight cycles or A340-28-4101, Revision
15,000 flight hours, whichever is first, after 01, dated August 16,
the most recent inspection, until paragraph (h) 2004.
of this AD is accomplished. For Airbus Model A340-28-4103, Revision
A330-201, -202, -203, -223, -243, -301, -321, - 02, dated April 1,
322, -323, -341, -342, and -343 airplanes: If a 2005.
float valve having P/N L87-13-002 is installed, A340-28-4111, dated
thereafter, replace that float valve with a April 6, 2005.
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 A330-201, -202, -203, -223, -243, -
301, -321, -322, -323, -341, -342, and -343
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 A330-201, -202, -203, -223, --243, -301, -321, -322, -
323, -341, -342, and -343 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-
201, -202, -203, -223, --243, -301, -321, -322, -323, -341, -342,
and -343 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 Airbus service bulletin
----------------------------------------------------------------------------------------------------------------
A330-201, -202, -203, -223, --243, - 62015-1............... A330-28-3088, dated April 27, 2004.
301, -321, -322, -323, -341, -342, L87-13-002............ A330-28-3089, Revision 02, dated April 1, 2005.
and -343 airplanes. L87-13-003............ A330-28-3093, dated June 16, 2005.
L87-13-003............ A330-28-3094, dated April 7, 2005.
A340-211, -212, -213, -311, -312, and 62015-1............... A340-28-4102, dated April 27, 2004.
--313 airplanes. L87-13-002............ A340-28-4103, Revision 02, dated April 1, 2005.
L87-13-003............ A340-28-4111, dated April 6, 2005.
A340-541-- and -642 airplanes........ 62015-1............... A340-28-5007, dated May 7, 2004.
L87-13-002............ A340-28-5010, dated may 7, 2004.
L87-13-003............ A340-28-5021, dated April 6, 2005.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 5976]]

Table 4.--Service Information for Actions Accomplished Previously
------------------------------------------------------------------------
Airbus model Airbus service bulletin
------------------------------------------------------------------------
A330-201, -202, -203, -223, -- A330-28-3087, dated July 24, 2003.
243, -301, -321, -322, -323, A330-28-3089, Revision 01, dated May 12,
-341, -342, and -343 2004.
airplanes.
A340-211, -212, -213, -311, - A340-28-4100, dated July 24, 2003.
312, and --313 airplanes. A340-28-4101, dated July 24, 2003.
A340-28-4103, Revision 01, dated May 12,
2004.
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)(1) 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.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.

Related Information

(l) French airworthiness 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.

Material Incorporated by Reference

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

Table 5.--Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A330-28-3086, excluding Appendix Original......... July 24, 2003.
01.
A330-28-3087, excluding Appendix 01............... August 16, 2004.
01.
A330-28-3088.................... Original......... April 27, 2004.
A330-28-3089.................... 02............... April 1, 2005.
A330-28-3093.................... Original......... June 16, 2005.
A330-28-3094.................... Original......... April 7, 2005.
A340-28-4100.................... 01............... August 16, 2004.
A340-28-4101, excluding Appendix 01............... August 16, 2004.
01.
A340-28-4102.................... Original......... April 27, 2004.
A340-28-4103.................... 02............... April 1, 2005.
A340-28-4111.................... Original......... April 6, 2005.
A340-28-5007.................... Original......... May 7, 2004.
A340-28-5010.................... Original......... May 7, 2004.
A340-28-5021.................... Original......... April 6, 2005.
------------------------------------------------------------------------

Issued in Renton, Washington, on January 27, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-989 Filed 2-3-06; 8:45 am]
BILLING CODE 4910-13-P

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