Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes; Airbus Model A330-300 Series Airplanes; and Airbus Model A340-200 and -300 Series Airplanes, 60655-60658 [2010-24711]

Download as PDF 60655 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Proposed Rules survey sample of at least 250 potential members, subscribers may use a sample of at least 30 potential members. (3) NCUA Form 4008—Organization Certificate. This document establishes the seven criteria required of subscribers by the Act and is signed by the subscribers and notarized. This document should be executed in duplicate. (4) NCUA Form 9501—Certification of Resolutions. This document certifies the board of the proposed corporate credit union has resolved to apply for federal insurance of member’s accounts and has authorized the chief executive officer and chief financial officer to execute the Application and Agreements for Insurance of Accounts. Both the chief executive officer and recording officer of the proposed corporate credit union must sign this certification. (5) NCUA Form 9500—Application and Agreements for Insurance of Accounts. This document contains agreements FCUs must comply with in order to obtain NCUA insurance coverage of member accounts. The document must be completed and signed by both the chief executive officer and chief financial officer. V—Name Selection It is the responsibility of the corporate FCU organizers to ensure that the proposed corporate FCU name does not constitute an infringement on the name of any corporation in its trade area. This responsibility also includes researching any service marks or trademarks used by any other corporation (including credit unions) in its trade area. NCUA will ensure, to the extent possible, that the corporate credit union’s name: • Is not already being officially used by another FCU; • Will not be confused with NCUA or another federal or state agency, or with another credit union; and • Does not include misleading or inappropriate language. The last three words in the name of every credit union chartered by NCUA must be ‘‘Federal Credit Union.’’ jlentini on DSKJ8SOYB1PROD with PROPOSALS VI—NCUA Review A—General OCCU will conduct an independent investigation of the corporate credit union’s charter application to assess the economic and long-term viability of the proposed corporate credit union. OCCU field staff will conduct the review and, if necessary, perform an on-site contact with selected officials and others having an interest in the proposed corporate credit union. The review will include evaluation of proposed management’s experience and VerDate Mar<15>2010 16:54 Sep 30, 2010 Jkt 223001 suitability, commitment of proposed officials, and assessment of economic viability. OCCU field staff may also be called upon to assist subscribers in the proper completion of required forms and the Organization Certificate—NCUA Form 4008. OCCU field staff will thoroughly analyze the prospective corporate credit union’s business plan for realistic projections, attainable goals, and time commitment. Any concerns will be reviewed with the subscribers and discussed with prospective officials. NCUA will follow the timeline set forth below in processing corporate charter applications: 1. Within 30 days of receipt of the charter package, OCCU field staff will meet with the proposed officials and management team to evaluate the adequacy of management and the information provided and to discuss the FCU’s ability to begin operations and meet their financial projections if the charter is approved. 2. On completion of all required reviews, but no later than 60 days after the meeting described above, OCCU field staff will make a recommendation to the OCCU Director regarding the charter application. The recommendation may include provisional requirements to be completed prior to final approval of a corporate FCU charter. 3. Within 30 days of receiving OCCU field staff recommendation, an OCCU analyst will determine if the application package can be forwarded to the NCUA Board for appropriate action, or if it should be returned to the subscribers. The subscribers will receive written notification of this decision. 4. Within 60 days after receipt of a complete application that addresses all of OCCU’s concerns, the NCUA Board will vote on the proposed charter. If the charter is approved, the officials must sign a ‘‘Letter of Understanding and Agreement’’ (LUA) before the corporate credit union can commence operations. This LUA will impose certain operational restrictions, require compliance with NCUA’s Rules and Regulations and adoption of the standard Corporate FCU Bylaws, and contain several financial performance milestones that the new charter must meet, consistent with Part 704. B—Finalization of New Charter If NCUA approves the charter application, the subscribers, as their final duty, will elect the board of directors for the newly chartered corporate FCU. The new board of directors will subsequently appoint the supervisory committee. The corporate PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 FCU must then submit a report of officials to OCCU. [FR Doc. 2010–24659 Filed 9–30–10; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0952; Directorate Identifier 2010–NM–131–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–201, –202, –203, –223, and –243 Airplanes; Airbus Model A330–300 Series Airplanes; and Airbus Model A340–200 and –300 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 88). By mail referenced 04/00/02/07/01–L296 of March 4th, 2002 and 04/00/02/07/03–L024 of February 3rd, 2003 the JAA [Joint Aviation Authorities] recommended to the National Aviation Authorities (NAA) the application of a similar regulation. The aim of this regulation is to require * * * a definition review against explosion hazards. * * * * * Failure of the auxiliary power unit (APU) bleed leak detection system could result in overheat of the fuel tank located in the horizontal stabilizer and ignition of the fuel vapors in that tank, which could result in a fuel tank explosion and consequent loss of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by November 15, 2010. You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. ADDRESSES: E:\FR\FM\01OCP1.SGM 01OCP1 60656 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Proposed Rules • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., 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 SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; e-mail airworthiness.A330–A340@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. jlentini on DSKJ8SOYB1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0952; Directorate Identifier 2010–NM–131–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We have lengthened the 30-day comment period for proposed ADs that VerDate Mar<15>2010 16:54 Sep 30, 2010 Jkt 223001 address MCAI originated by aviation authorities of other countries to provide adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0089, dated May 10, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 88). By mail referenced 04/00/02/07/01–L296 of March 4th, 2002 and 04/00/02/07/03–L024 of February 3rd, 2003 the JAA [Joint Aviation Authorities] recommended to the National Aviation Authorities (NAA) the application of a similar regulation. The aim of this regulation is to require all holders of type certificates for transport aircraft certified after 01 January 1958 with a capacity of 30 passengers or more, or a payload of 3,402 kg or more, to carry out a definition review against explosion hazards. To be compliant with SFAR88/JAA INT/ POL 25/12 requirements, this AD requires the installation of the updated FWC [flight warning computer] software standard which ensures correct operation of the APU bleed leak detection system before each flight. Failure of the auxiliary power unit (APU) bleed leak detection system could result in overheat of the fuel tank located in the horizontal stabilizer and ignition of the fuel vapors in that tank, which could result in a fuel tank explosion and consequent loss of the airplane. You may obtain further information by examining the MCAI in the AD docket. The FAA has examined the underlying safety issues involved in 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’’ (66 FR 23086, May 7, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 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 (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 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 a 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 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. E:\FR\FM\01OCP1.SGM 01OCP1 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Proposed Rules 60657 Relevant Service Information Airbus has issued the service information identified in the table below. RELEVANT SERVICE INFORMATION Airbus Service Bulletin— Revision— Dated— A330–31–3125 ...................................................................... A330–31–3146, including Appendix 01 ................................ A340–31–4111 ...................................................................... A340–31–4125 ...................................................................... Original ................................................................................. 01 ......................................................................................... Original ................................................................................. 01 ......................................................................................... December 31, 2008. May 5, 2010. February 5, 2007. December 9, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. jlentini on DSKJ8SOYB1PROD with PROPOSALS Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 53 products of U.S. registry. We also estimate that it would take about 5 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Where the service information lists required parts costs that are covered VerDate Mar<15>2010 16:54 Sep 30, 2010 Jkt 223001 under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $22,525, or $425 per product. 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 and placed it in the AD docket. Authority for This Rulemaking List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 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 this 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 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2010–0952; Directorate Identifier 2010–NM–131–AD. Comments Due Date (a) We must receive comments by November 15, 2010. Affected ADs (b) None. Applicability (c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342 and –343 airplanes, all manufacturer serial numbers except those on which Airbus modification 51790 has been embodied in production or Airbus Service Bulletin A330–31–3066, A330–31–3082, A330–31–3093, or A330–31–3105 has been embodied in service; certificated in any category. (2) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes, all E:\FR\FM\01OCP1.SGM 01OCP1 60658 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Proposed Rules manufacturer serial numbers; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 31: Instruments. Reason (e) The mandatory continuing airworthiness information (MCAI) states: [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 88). By mail referenced 04/00/02/07/01–L296 of March 4th, 2002 and 04/00/02/07/03–L024 of February 3rd, 2003 the JAA [Joint Aviation Authorities] recommended to the National Aviation Authorities (NAA) the application of a similar regulation. The aim of this regulation is to require * * * a definition review against explosion hazards. * * * * * Failure of the auxiliary power unit (APU) bleed leak detection system could result in overheat of the fuel tank located in the horizontal stabilizer and ignition of the fuel vapors in that tank, which could result in a fuel tank explosion and consequent loss of the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) Within 6 months after the effective date of this AD, do the applicable actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) For Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342 and –343 airplanes: Install flight warning computer (FWC) software standard T3 (part number (P/N) LA2E20202T30000) on both FWCs, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–31–3146, including Appendix 01, Revision 01, dated May 5, 2010. (2) For Model A340–211, –212, –213, –311, –312, and –313 airplanes: Install FWC software standard L11 (P/N LA2E0060D110000) on both FWCs, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 31–4125, Revision 01, dated December 9, 2008. (h) Prior to or concurrently with accomplishing the corresponding requirements of paragraph (g) of this AD, install FWC software standard T2–0 in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 31–3125, dated December 31, 2008 (for Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342 and –343 airplanes). (i) Prior to or concurrently with accomplishing the corresponding requirements of paragraph (g) of this AD, install FWC software standard L10–1 in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 31–4111, dated February 5, 2007 (for Model A340–211, –212, –213, –311, –312, and –313 airplanes). (j) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A330–31–3146, dated February 2, 2010; or A340–31–4125, dated October 27, 2008; are acceptable for compliance with the corresponding requirements of paragraph (g) of this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (k) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (l) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0089, dated May 10, 2010, and the service information identified in Table 1 of this AD, for related information. TABLE 1—RELATED SERVICE INFORMATION Airbus Service Bulletin— Revision— Dated— A330–31–3125 ..................................................................................................... A330–31–3146, including Appendix 01 ............................................................... A340–31–4111 ..................................................................................................... A340–31–4125 ..................................................................................................... Original .................................................. 01 .......................................................... Original .................................................. 01 .......................................................... December 31, 2008. May 5, 2010. February 5, 2007. December 9, 2008. Issued in Renton, Washington on September 23, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. jlentini on DSKJ8SOYB1PROD with PROPOSALS [FR Doc. 2010–24711 Filed 9–30–10; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 18:05 Sep 30, 2010 Jkt 223001 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 E:\FR\FM\01OCP1.SGM 01OCP1

Agencies

[Federal Register Volume 75, Number 190 (Friday, October 1, 2010)]
[Proposed Rules]
[Pages 60655-60658]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-24711]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0952; Directorate Identifier 2010-NM-131-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-201, -202, -203, -
223, and -243 Airplanes; Airbus Model A330-300 Series Airplanes; and 
Airbus Model A340-200 and -300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

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

    [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 
88).
    By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and 
04/00/02/07/03-L024 of February 3rd, 2003 the JAA [Joint Aviation 
Authorities] recommended to the National Aviation Authorities (NAA) 
the application of a similar regulation.
    The aim of this regulation is to require * * * a definition 
review against explosion hazards.
* * * * *

Failure of the auxiliary power unit (APU) bleed leak detection system 
could result in overheat of the fuel tank located in the horizontal 
stabilizer and ignition of the fuel vapors in that tank, which could 
result in a fuel tank explosion and consequent loss of the airplane. 
The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by November 15, 
2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.

[[Page 60656]]

     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., 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 SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; e-mail airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0952; 
Directorate Identifier 2010-NM-131-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We have lengthened the 30-day comment period for proposed ADs that 
address MCAI originated by aviation authorities of other countries to 
provide adequate time for interested parties to submit comments. The 
comment period for these proposed ADs is now typically 45 days, which 
is consistent with the comment period for domestic transport ADs.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2010-0089, dated May 10, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 
88).
    By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and 
04/00/02/07/03-L024 of February 3rd, 2003 the JAA [Joint Aviation 
Authorities] recommended to the National Aviation Authorities (NAA) 
the application of a similar regulation.
    The aim of this regulation is to require all holders of type 
certificates for transport aircraft certified after 01 January 1958 
with a capacity of 30 passengers or more, or a payload of 3,402 kg 
or more, to carry out a definition review against explosion hazards.
    To be compliant with SFAR88/JAA INT/POL 25/12 requirements, this 
AD requires the installation of the updated FWC [flight warning 
computer] software standard which ensures correct operation of the 
APU bleed leak detection system before each flight.

Failure of the auxiliary power unit (APU) bleed leak detection system 
could result in overheat of the fuel tank located in the horizontal 
stabilizer and ignition of the fuel vapors in that tank, which could 
result in a fuel tank explosion and consequent loss of the airplane. 
You may obtain further information by examining the MCAI in the AD 
docket.
    The FAA has examined the underlying safety issues involved in 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'' 
(66 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 (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 
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 a 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 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.

[[Page 60657]]

Relevant Service Information

    Airbus has issued the service information identified in the table 
below.

                                          Relevant Service Information
----------------------------------------------------------------------------------------------------------------
        Airbus Service Bulletin--                   Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
A330-31-3125.............................  Original....................  December 31, 2008.
A330-31-3146, including Appendix 01......  01..........................  May 5, 2010.
A340-31-4111.............................  Original....................  February 5, 2007.
A340-31-4125.............................  01..........................  December 9, 2008.
----------------------------------------------------------------------------------------------------------------

The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 53 products of U.S. registry. We also estimate that 
it would take about 5 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $0 per product. Where the 
service information lists required parts costs that are covered under 
warranty, we have assumed that there will be no charge for these costs. 
As we do not control warranty coverage for affected parties, some 
parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $22,525, or $425 per product.

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 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 this 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 and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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:

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 AD:

Airbus: Docket No. FAA-2010-0952; Directorate Identifier 2010-NM-
131-AD.

Comments Due Date

    (a) We must receive comments by November 15, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342 and -343 airplanes, all 
manufacturer serial numbers except those on which Airbus 
modification 51790 has been embodied in production or Airbus Service 
Bulletin A330-31-3066, A330-31-3082, A330-31-3093, or A330-31-3105 
has been embodied in service; certificated in any category.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes, all

[[Page 60658]]

manufacturer serial numbers; certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 31: 
Instruments.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    [T]he FAA published SFAR 88 (Special Federal Aviation Regulation 
88).
    By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and 
04/00/02/07/03-L024 of February 3rd, 2003 the JAA [Joint Aviation 
Authorities] recommended to the National Aviation Authorities (NAA) 
the application of a similar regulation.
    The aim of this regulation is to require * * * a definition 
review against explosion hazards.
* * * * *
Failure of the auxiliary power unit (APU) bleed leak detection 
system could result in overheat of the fuel tank located in the 
horizontal stabilizer and ignition of the fuel vapors in that tank, 
which could result in a fuel tank explosion and consequent loss of 
the airplane.

Compliance

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

Actions

    (g) Within 6 months after the effective date of this AD, do the 
applicable actions specified in paragraphs (g)(1) and (g)(2) of this 
AD.
    (1) For Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342 and -343 airplanes: Install flight 
warning computer (FWC) software standard T3 (part number (P/N) 
LA2E20202T30000) on both FWCs, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-31-3146, including 
Appendix 01, Revision 01, dated May 5, 2010.
    (2) For Model A340-211, -212, -213, -311, -312, and -313 
airplanes: Install FWC software standard L11 (P/N LA2E0060D110000) 
on both FWCs, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A340-31-4125, Revision 01, dated December 9, 
2008.
    (h) Prior to or concurrently with accomplishing the 
corresponding requirements of paragraph (g) of this AD, install FWC 
software standard T2-0 in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-31-3125, dated December 
31, 2008 (for Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342 and -343 airplanes).
    (i) Prior to or concurrently with accomplishing the 
corresponding requirements of paragraph (g) of this AD, install FWC 
software standard L10-1 in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A340-31-4111, dated February 
5, 2007 (for Model A340-211, -212, -213, -311, -312, and -313 
airplanes).
    (j) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A330-31-3146, dated February 
2, 2010; or A340-31-4125, dated October 27, 2008; are acceptable for 
compliance with the corresponding requirements of paragraph (g) of 
this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (k) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: 
Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (l) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2010-0089, dated May 10, 2010, and the 
service information identified in Table 1 of this AD, for related 
information.

                                      Table 1--Related Service Information
----------------------------------------------------------------------------------------------------------------
        Airbus Service Bulletin--                   Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
A330-31-3125.............................  Original....................  December 31, 2008.
A330-31-3146, including Appendix 01......  01..........................  May 5, 2010.
A340-31-4111.............................  Original....................  February 5, 2007.
A340-31-4125.............................  01..........................  December 9, 2008.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington on September 23, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-24711 Filed 9-30-10; 8:45 am]
BILLING CODE 4910-13-P