Airworthiness Directives; Airbus Model A300-600 Series Airplanes, 43199-43202 [07-3774]

Download as PDF 43199 Proposed Rules Federal Register Vol. 72, No. 149 Friday, August 3, 2007 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF AGRICULTURE Rural Utilities Service 7 CFR Part 1739 RIN 0572–AC09 Community Connect Broadband Grant Program Rural Utilities Service, USDA. ACTION: Proposed rule. pwalker on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: The Rural Utilities Service, an agency delivering the United States Department of Agriculture’s Rural Development Utilities Program, hereinafter referred to as Rural Development and/or the Agency, is issuing proposed regulations to amend its Community-Oriented Connectivity Broadband Grant Program (Community Connect Broadband Grant Program). The Agency has determined that expanding the resource materials used to determine community eligibility for the program will result in a larger number of eligible communities. In addition, Rural Development has changed the test for economic hardship, allowing the applicant community’s median household income to be compared to that of its state, which is also expected to increase the number of eligible applicants. Lastly, the Agency is proposing to amend its regulations to specify operating expenses which are approved for grant funding. This proposed rule is not applicable to Community Connect grant applications filed for funding during fiscal year 2007. In the Rules and Regulations section of this Federal Register, the Agency is publishing this action as a direct final rule without prior proposal because the Agency views this as a noncontroversial action and anticipates no adverse comments. If no adverse comments are received in response to the direct final rule, no further action will be taken on this proposed rule and the action will become effective at the time specified in the direct final rule. If the Agency receives adverse comments, a timely document will be published in VerDate Aug<31>2005 16:21 Aug 02, 2007 Jkt 211001 the Federal Register and all public comments received will be addressed in a subsequent final rule on this action. DATES: Comments on this proposed rule must be received by the Agency or carry a postmark or equivalent no later than September 4, 2007. ADDRESSES: Submit comments by either of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and, in the lower ‘‘Search Regulations and Federal Actions’’ box, select ‘‘Rural Utilities Service’’ from the agency drop-down menu, then click on ‘‘Submit.’’ In the Docket ID column, select RUS–07– Telecom–0008 to submit or view public comments and to view supporting and related materials available electronically. Information on using Regulations.gov, including instructions for accessing documents, submitting comments, and viewing the docket after the close of the comment period, is available through the site’s ‘‘User Tips’’ link. • Postal Mail/Commercial Delivery: Please send your comment addressed to Michele Brooks, Acting Deputy Director, Program Development and Regulatory Analysis, USDA Rural Development, STOP 1522, Room 5159, 1400 Independence Avenue, Washington, DC 20250–1522. Please state that your comment refers to Docket No. RUS–07– Telecom–0008. Other Information: Additional information about Rural Development and its programs is available at https:// www.rurdev.usda.gov/. FOR FURTHER INFORMATION CONTACT: Kenneth Kuchno, Director, Broadband Division, USDA Rural Development Utilities Program, STOP 1599, 1400 Independence Avenue, SW., Washington, DC 20250–1599, Telephone (202) 690–4673, Facsimile (202) 690–4389. E-mail address: kenneth.kuchno@usda.gov. SUPPLEMENTARY INFORMATION: For applicable supplementary information on this action, see the SUPPLEMENTARY INFORMATION provided in the direct final rule located in the Rules and Regulations section of this Federal Register. Dated: July 19, 2007. James M. Andrew, Administrator, Rural Utilities Service. [FR Doc. E7–15108 Filed 8–2–07; 8:45 am] BILLING CODE 3410–15–P PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28853; Directorate Identifier 2006–NM–218–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300–600 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: At some locations, the new calculated fatigue life [for the wing to center box assembly] falls below the aircraft Design Service Goal. The aim of this Airworthiness Directive (AD) is * * * to ensure detection of cracks on the panels and stiffeners at rib No. 1. This situation, if left uncorrected, could affect the structural integrity of the area. 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 September 4, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • 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: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. E:\FR\FM\03AUP1.SGM 03AUP1 43200 Federal Register / Vol. 72, No. 149 / Friday, August 3, 2007 / Proposed Rules Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.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: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: pwalker on PROD1PC71 with PROPOSALS Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. 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–2007–28853; Directorate Identifier 2006–NM–218–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 will post all comments we receive, without change, to https:// dms.dot.gov. including any personal information you provide. We will also post a report summarizing each VerDate Aug<31>2005 16:21 Aug 02, 2007 Jkt 211001 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 2006–0257, dated August 24, 2006 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During installation of the wing to the centre box junction on the Final Assembly Line, some ‘‘taperlocks’’ fasteners were found non compliant with the specification. Fatigue tests on samples and calculation performed on non-conform fasteners demonstrated that this defect could lead to decrease the fatigue lift of the wing to centre wing box assembly. At some locations, the new calculated fatigue life falls below the aircraft Design Service Goal. The aim of this Airworthiness Directive (AD) is to mandate repetitive inspections to ensure detection of cracks on the panels and stiffeners at rib No. 1. This situation, if left uncorrected, could affect the structural integrity of the area. The corrective action includes contacting Airbus for repair instructions in the event of crack finding. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletin A300–53–6154, including Appendix 01, dated June 20, 2006, and A300–600 Airworthiness Limitations Items Document AI/SE–M2/95A.0502/06, Issue 11, dated April 2006. 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 Unitejd 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 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 7 products of U.S. registry. We also estimate that it would take about 79 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $44,240, or $6,320 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; E:\FR\FM\03AUP1.SGM 03AUP1 Federal Register / Vol. 72, No. 149 / Friday, August 3, 2007 / Proposed Rules 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 the4 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, 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2007–28853; Directorate Identifier 2006–NM–218–AD. Comments Due Date (a) We must receive comments by September 4, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300– 600 series airplanes, manufacturing serial number (MSN) 0815 up to MSN 0821 inclusive, certificated in any category. pwalker on PROD1PC71 with PROPOSALS Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: During installation of the wing to the centre box junction on the Final Assembly Line, some ‘‘taperlocks’’ fasteners were found non compliant with the specification. Fatigue tests on samples and calculation performed on non-conform fasteners demonstrated that this defect could lead to decrease the fatigue life of the wing to centre wing box assembly. At some locations, the new calculated fatigue life falls below the aircraft Design Service Goal. The aim of this Airworthiness Directive (AD) is to mandate repetitive inspections to ensure detection of cracks on the panels and stiffeners at rib No. 1 This situation, if left uncorrected, could affect the structural integrity of the area. VerDate Aug<31>2005 16:54 Aug 02, 2007 Jkt 211001 The corrective action includes contacting Airbus for repair instructions in the event of crack finding. Actions and Compliance (f) Unless already done, do the following actions. (1) Action No. 1, for the center wing box: (i) At the later of the times in paragraphs (f)(1)(i)(A) and (f)(1)(i)(B): Do an external ultrasonic inspection for cracking of the taperlocks fasteners of the center wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6154, including appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 19,800 total flight cycles or 41,200 flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 3,300 flight cycles or 6,900 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6154, including Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(1)(ii) of this AD is valid until the threshold of Airbus A300–600 Airworthiness Limitation Items (ALI) Task 571006–02–1 is reached. After reaching this threshold, the ultrasonic inspection is to be done according to Task 571006–02–1, ‘‘Special detailed inspection (Ultrasonic) of wing junction at rib 1 horizontal flange of lower T section, between FR40 and FR47 inboard side, LH/RH,’’ of Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/95A.0502/06, Issue 11, dated April 2006. (2) Action No. 2, for the outer wing box: (i) At the later of the times in paragraphs (f)(2)(i)(A) and (f)(2)(i)(B): Do an external ultrasonic inspection for cracking of the taperlocks fasteners of the outer wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6154, including Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 15,200 total flight cycles or 31,700 flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 3,700 flight cycles or 7,700 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6154, including Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(2)(ii) of this AD is valid until reaching the threshold of Airbus A300–600 Airworthiness Limitation Items (ALI) Task 571022–01–2, ‘‘Special detailed inspection (Ultrasonic) of wing-fuselage lower skin splice at rib 1 (wing side).’’ After reaching this threshold, the ultrasonic inspection is to be done according to Task 571022–01–2 of PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 43201 Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/95A.0502/06, Issue 11, dated April 2006. (3) Action No. 3, for the outer wing box: (i) At the later of the times in paragraphs (f)(3)(i)(A) and (f)(3)(i)(B): Do an internal x-ray inspection for cracking of the taperlocks fasteners of the outer wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6154, including Appendix 01, dated June 20, 2006. If any crack is detected: Before further flight, contact Airbus for repair instructions, and repair. (A) Before the accumulation of 20,900 total flight cycles or 43,400 flight hours, whichever occurs first. (B) Within 3 months after the effective date of this AD. (ii) Repeat the inspection thereafter at intervals not to exceed 1,800 flight cycles or 3,700 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6154, including Appendix 01, dated June 20, 2006. (iii) The repetitive interval specified in paragraph (f)(3)(ii) of this AD is valid until reaching the threshold of Airbus A300–600 Airworthiness Limitation Items (ALI) Task 571022–02–2, ‘‘Special detailed inspection (x-ray) of wing-fuselage lower skin splice at rib 1 (wing side).’’ After reaching this threshold, the x-ray inspection is to be done according to Task 5710022–02–2 of Airbus A300–60 Airworthiness Limitation Items Document AI/SE–M2/95A.0502/06, Issue 11, dated April 2006. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Tom Stafford, Aerospace Engineer, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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, the Office of Management and Budget (OMB) has approved the information collection E:\FR\FM\03AUP1.SGM 03AUP1 43202 Federal Register / Vol. 72, No. 149 / Friday, August 3, 2007 / Proposed Rules requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAIEASA Airworthiness Directive 2006–0257, dated August 24, 2006; Airbus Service Bulletin A300–53–6154, including Appendix 01, dated June 20, 2006; and Airbus A300–600 Airworthiness Limitations Items Document AI/SE–M2/ 95A.0502/06, Issue 11, dated April 2006; for related information. Issued in Renton, Washington, on July 25, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 07–3774 Filed 8–2–07; 8:45 am] BILLING CODE 4910–13–M SOCIAL SECURITY ADMINISTRATION [Docket No. SSA 2007–0040] also deliver them to the Office of Regulations, Social Security Administration, 107 Altmeyer Building, 6401 Security Boulevard, Baltimore, MD 21235–6401, between 8 a.m. and 4:30 p.m. on regular business days. Comments are posted on the Federal eRulemaking Portal, or you may inspect them physically on regular business days by making arrangements with the contact person shown in this preamble. FOR FURTHER INFORMATION CONTACT: Ines Riley, Social Insurance Specialist, Office of Income Security Programs, Social Security Administration, RRCC #126, 6401 Security Boulevard, Baltimore, Maryland 21235–6401, (410) 965–4138. For information on eligibility or filing for benefits, call our national toll-free number, 1–800–772–1213 or TTY 1– 800–325–0778, or visit our Internet site, Social Security Online, at https:// www.socialsecurity.gov. 20 CFR Part 404 SUPPLEMENTARY INFORMATION: RIN 0960–AG50 Electronic Version Sixty-Month Period of Employment Requirement for Government Pension Offset Exemption The electronic file of this document is available on the date of publication in the Federal Register at https:// www.gpoaccess.gov/fr/. AGENCY: Social Security Administration (SSA). pwalker on PROD1PC71 with PROPOSALS ACTION: Notice of proposed rulemaking. SUMMARY: To implement section 418 of the Social Security Protection Act of 2004 (SSPA), we propose to revise our regulations to explain that a State or local government worker will be subject to the Government Pension Offset (GPO) provision under title II of the Social Security Act (the Act), if any part of the last 60 months of government service was not covered by Social Security. We also propose to replace the words ‘‘receiving’’ and ‘‘received’’ with the word ‘‘payable’’ when referring to the eligibility to or payout from a government pension. This wording change will make the regulatory and statutory language consistent and help clarify when the GPO is applicable. In addition, we propose to revise our regulations to reflect a separate 60month requirement that was made applicable to Federal employees by a 1987 law. DATES: To be sure that we consider your comments, we must receive them by October 2, 2007. ADDRESSES: You may give us your comments by: Internet through the Federal eRulemaking Portal at https:// www.regulations.gov; e-mail to regulations@ssa.gov; telefax to (410) 966–2830; or letter to the Commissioner of Social Security, P.O. Box 17703, Baltimore, MD 21235–7703. You may VerDate Aug<31>2005 16:21 Aug 02, 2007 Jkt 211001 Background If you receive a pension from a Federal, State or local government that is based on work that was not covered by Social Security, then the GPO may reduce certain kinds of Social Security benefits that you might also be eligible to receive. The GPO applies to Social Security wife’s, husband’s, widow’s, widower’s, mother’s or father’s, and divorced or surviving divorced spouse’s benefits. For the sake of simplicity, these benefits are often referred to as spouse’s benefits, even though other benefits, as described in the previous sentence, are affected. These benefits may be reduced, to zero if necessary, by two-thirds of the amount of your government pension from noncovered work. See section 202(k)(5) of the Act, codified at 42 U.S.C. 402(k)(5). The GPO does not apply to Social Security retirement or disability benefits that you earned through your own covered employment. The GPO was enacted in 1977 to reduce the Social Security spouse’s benefit of workers who have a government pension based on noncovered employment. Congress believed that persons who received a government pension based on their own noncovered work would receive a ‘‘windfall’’ if they also could receive unreduced Social Security spouse’s benefits, regardless of their dependency on the insured spouse. (See S. Rep. No. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 95–572, 95th Cong., 1st Sess., at 28.) The GPO treats these government workers similar to workers in jobs covered by Social Security. Workers who earn their own Social Security retirement benefit, and who are eligible to receive a spouse’s benefit, have the spouse’s benefit, in effect, offset by their retirement benefit. They receive the larger of the two benefits. They do not receive both their own Social Security retirement benefit and a spouse’s benefit. Therefore, the GPO prevents individuals who receive a government pension based on noncovered earnings from receiving more in combined pension and Social Security spouse’s benefits than individuals who worked in covered employment and also were eligible for spouse’s benefits. The GPO adjusts the spouse’s benefit of a government worker to prevent a ‘‘windfall.’’ (See H. Rep. No. 100–391(I), 100th Cong., 2nd Sess., at 2313–466.) Before enactment of the SSPA, Public Law 108–203, on March 2, 2004, the law allowed an exception to the application of the GPO, referred to as the ‘‘last day’’ exception. Under this exception, State or local government workers could avoid application of the GPO by working 1 day in Social Security covered employment at the end of their career. Section 418 of the SSPA phases out the ‘‘last day’’ exception. Applications for spouse’s benefits filed on or after April 1, 2004 will be subject to the GPO unless the individual’s last 60 months of government employment are covered by Social Security. Therefore, if there is any noncovered government employment during the last 60 months of government service on which a pension is based, the GPO will apply. State or local government workers who filed an application for spouse’s benefits before April 1, 2004, or whose last day of government employment was before July 1, 2004, are exempt from the GPO if they worked in covered employment on the last day of the government service on which their pension is based. The last 60-month requirement established by section 418 of the SSPA is similar to a requirement established by the Omnibus Budget Reconciliation Act of 1987 (OBRA 1987), Public Law 100–203, section 9007. That law specified that Federal employees who transfer from the Civil Service Retirement System to the new Federal Employees Retirement System must work for at least 60 months in the aggregate in covered employment in order to avoid application of the GPO. For workers whose last day of State or local government employment occurs within 5 years after the date of E:\FR\FM\03AUP1.SGM 03AUP1

Agencies

[Federal Register Volume 72, Number 149 (Friday, August 3, 2007)]
[Proposed Rules]
[Pages 43199-43202]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-3774]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28853; Directorate Identifier 2006-NM-218-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 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:

    At some locations, the new calculated fatigue life [for the wing 
to center box assembly] falls below the aircraft Design Service 
Goal.
    The aim of this Airworthiness Directive (AD) is * * * to ensure 
detection of cracks on the panels and stiffeners at rib No. 1. This 
situation, if left uncorrected, could affect the structural 
integrity of the area.

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 September 4, 
2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Fax: (202) 493-2251.
     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: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: https://www.regulations.gov. 
Follow the instructions for submitting comments.

[[Page 43200]]

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
dms.dot.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: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This proposed AD references the MCAI and related service 
information that we considered in forming the engineering basis to 
correct the unsafe condition. The proposed AD contains text copied from 
the MCAI and for this reason might not follow our plain language 
principles.

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-2007-
28853; Directorate Identifier 2006-NM-218-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 will post all comments we receive, without change, to https://
dms.dot.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 2006-0257, dated August 24, 2006 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During installation of the wing to the centre box junction on 
the Final Assembly Line, some ``taperlocks'' fasteners were found 
non compliant with the specification.
    Fatigue tests on samples and calculation performed on non-
conform fasteners demonstrated that this defect could lead to 
decrease the fatigue lift of the wing to centre wing box assembly.
    At some locations, the new calculated fatigue life falls below 
the aircraft Design Service Goal.
    The aim of this Airworthiness Directive (AD) is to mandate 
repetitive inspections to ensure detection of cracks on the panels 
and stiffeners at rib No. 1. This situation, if left uncorrected, 
could affect the structural integrity of the area.

The corrective action includes contacting Airbus for repair 
instructions in the event of crack finding. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A300-53-6154, including Appendix 
01, dated June 20, 2006, and A300-600 Airworthiness Limitations Items 
Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. 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 Unitejd 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 7 products of U.S. registry. We also estimate that 
it would take about 79 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $44,240, or $6,320 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;

[[Page 43201]]

    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 the4 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, 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-2007-28853; Directorate Identifier 2006-NM-
218-AD.

Comments Due Date

    (a) We must receive comments by September 4, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300-600 series airplanes, 
manufacturing serial number (MSN) 0815 up to MSN 0821 inclusive, 
certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    During installation of the wing to the centre box junction on 
the Final Assembly Line, some ``taperlocks'' fasteners were found 
non compliant with the specification.
    Fatigue tests on samples and calculation performed on non-
conform fasteners demonstrated that this defect could lead to 
decrease the fatigue life of the wing to centre wing box assembly.
    At some locations, the new calculated fatigue life falls below 
the aircraft Design Service Goal.
    The aim of this Airworthiness Directive (AD) is to mandate 
repetitive inspections to ensure detection of cracks on the panels 
and stiffeners at rib No. 1 This situation, if left uncorrected, 
could affect the structural integrity of the area.
    The corrective action includes contacting Airbus for repair 
instructions in the event of crack finding.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Action No. 1, for the center wing box:
    (i) At the later of the times in paragraphs (f)(1)(i)(A) and 
(f)(1)(i)(B): Do an external ultrasonic inspection for cracking of 
the taperlocks fasteners of the center wing box, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
6154, including appendix 01, dated June 20, 2006. If any crack is 
detected: Before further flight, contact Airbus for repair 
instructions, and repair.
    (A) Before the accumulation of 19,800 total flight cycles or 
41,200 flight hours, whichever occurs first.
    (B) Within 3 months after the effective date of this AD.
    (ii) Repeat the inspection thereafter at intervals not to exceed 
3,300 flight cycles or 6,900 flight hours, whichever occurs first, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6154, including Appendix 01, dated June 20, 2006.
    (iii) The repetitive interval specified in paragraph (f)(1)(ii) 
of this AD is valid until the threshold of Airbus A300-600 
Airworthiness Limitation Items (ALI) Task 571006-02-1 is reached. 
After reaching this threshold, the ultrasonic inspection is to be 
done according to Task 571006-02-1, ``Special detailed inspection 
(Ultrasonic) of wing junction at rib 1 horizontal flange of lower T 
section, between FR40 and FR47 inboard side, LH/RH,'' of Airbus 
A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/
06, Issue 11, dated April 2006.
    (2) Action No. 2, for the outer wing box:
    (i) At the later of the times in paragraphs (f)(2)(i)(A) and 
(f)(2)(i)(B): Do an external ultrasonic inspection for cracking of 
the taperlocks fasteners of the outer wing box, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
6154, including Appendix 01, dated June 20, 2006. If any crack is 
detected: Before further flight, contact Airbus for repair 
instructions, and repair.
    (A) Before the accumulation of 15,200 total flight cycles or 
31,700 flight hours, whichever occurs first.
    (B) Within 3 months after the effective date of this AD.
    (ii) Repeat the inspection thereafter at intervals not to exceed 
3,700 flight cycles or 7,700 flight hours, whichever occurs first, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6154, including Appendix 01, dated June 20, 2006.
    (iii) The repetitive interval specified in paragraph (f)(2)(ii) 
of this AD is valid until reaching the threshold of Airbus A300-600 
Airworthiness Limitation Items (ALI) Task 571022-01-2, ``Special 
detailed inspection (Ultrasonic) of wing-fuselage lower skin splice 
at rib 1 (wing side).'' After reaching this threshold, the 
ultrasonic inspection is to be done according to Task 571022-01-2 of 
Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/
95A.0502/06, Issue 11, dated April 2006.
    (3) Action No. 3, for the outer wing box:
    (i) At the later of the times in paragraphs (f)(3)(i)(A) and 
(f)(3)(i)(B): Do an internal x-ray inspection for cracking of the 
taperlocks fasteners of the outer wing box, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6154, 
including Appendix 01, dated June 20, 2006. If any crack is 
detected: Before further flight, contact Airbus for repair 
instructions, and repair.
    (A) Before the accumulation of 20,900 total flight cycles or 
43,400 flight hours, whichever occurs first.
    (B) Within 3 months after the effective date of this AD.
    (ii) Repeat the inspection thereafter at intervals not to exceed 
1,800 flight cycles or 3,700 flight hours, whichever occurs first, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6154, including Appendix 01, dated June 20, 2006.
    (iii) The repetitive interval specified in paragraph (f)(3)(ii) 
of this AD is valid until reaching the threshold of Airbus A300-600 
Airworthiness Limitation Items (ALI) Task 571022-02-2, ``Special 
detailed inspection (x-ray) of wing-fuselage lower skin splice at 
rib 1 (wing side).'' After reaching this threshold, the x-ray 
inspection is to be done according to Task 5710022-02-2 of Airbus 
A300-60 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/
06, Issue 11, dated April 2006.

FAA AD Differences

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

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Tom Stafford, Aerospace Engineer, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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, the 
Office of Management and Budget (OMB) has approved the information 
collection

[[Page 43202]]

requirements and has assigned OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAIEASA Airworthiness Directive 2006-0257, dated 
August 24, 2006; Airbus Service Bulletin A300-53-6154, including 
Appendix 01, dated June 20, 2006; and Airbus A300-600 Airworthiness 
Limitations Items Document AI/SE-M2/95A.0502/06, Issue 11, dated 
April 2006; for related information.

    Issued in Renton, Washington, on July 25, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 07-3774 Filed 8-2-07; 8:45 am]
BILLING CODE 4910-13-M