Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes, 11067-11069 [E8-3823]

Download as PDF rfrederick on PROD1PC67 with PROPOSALS Federal Register / Vol. 73, No. 41 / Friday, February 29, 2008 / Proposed Rules www.Regulations.gov. Comments may be submitted by e-mail to Mike.Soboroff@hq.doe.gov. Comments may be mailed to: Mike Soboroff, U.S. Department of Energy, Office of Electricity and Energy Assurance, OE– 30, 1000 Independence Avenue, SW., Washington, DC 20585. Comments by e-mail are encouraged. FOR FURTHER INFORMATION CONTACT: Mike Soboroff at (202) 586–4936 or via e-mail at Mike.Soboroff@hq.doe.gov. SUPPLEMENTARY INFORMATION: This NOPR proposes to amend DOE regulations at 10 CFR part 216, which implement DOE’s delegated authority under section 101(c) of the DPA. Section 101(c) provides authority to require the allocation of, or priority performance under contracts or orders relating to, materials and equipment, services, or facilities, in order to maximize domestic energy supplies, if DOE and the Department of Commerce make certain findings. The NOPR would make a number of technical changes to part 216 regulations to reflect a 1991 amendment, which broadens the scope of authority in section 101(c), and Executive Order 12919, (June 3, 1994). The NOPR also proposes conforming changes in the Department of Energy Acquisition Regulation at 48 CFR parts 911 and 952. Today, DOE is also publishing, elsewhere in this issue of the Federal Register, a direct final rule that makes changes to the DOE regulations regarding materials allocation and priority performance under contracts or orders to maximize domestic energy supplies. The amendments in the direct final rule are identical to the amendments that are being proposed in this NOPR. As explained in the preamble of the direct final rule, DOE considers these amendments to be noncontroversial and unlikely to generate any significant adverse comments. If no significant adverse comments are received by DOE on the amendments, the direct final rule will become effective on the date specified in that rule, and there will be no further action on this proposal. If significant adverse comments are timely received on the direct final rule, the direct final rule will be withdrawn. The public comments will then be addressed in a subsequent final rule based on the rule proposed in this NOPR. Because DOE will not institute a second comment period on this proposed rule, any party interested in commenting should do so during this comment period. For further supplemental information, the detailed rationale, and the rule amendment, see the information VerDate Aug<31>2005 15:34 Feb 28, 2008 Jkt 214001 provided in the direct final rule in this issue of the Federal Register. List of Subjects 10 CFR Part 216 Energy, Government contracts, Reporting and recordkeeping requirements, Strategic and critical materials. 48 CFR Part 911 Government procurement. 48 CFR Part 952 Government procurement, Reporting and recordkeeping requirements. Issued in Washington, DC on February 20, 2008. Edward R. Simpson, Director, Office of Procurement and Assistance Management, Department of Energy. William N. Bryan, Deputy Assistant Secretary, Infrastructure Security and Energy Restoration, Department of Energy. David O. Boyd, Director, Office of Acquisition and Supply Management, National Nuclear Security Administration. [FR Doc. E8–3776 Filed 2–28–08; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0222; Directorate Identifier 2007–NM–300–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 and 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: Due to several crack findings in the area of wing centre box lower aft corner at FR47, this area of structure has been subjected to accomplishment of several inspection Service Bulletins rendered mandatory in accordance with Airworthiness Limitation Items requirement for A300 aircraft and PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 11067 Airworthiness Directive (AD) F–2004–159 for A300–600 aircraft [which corresponds to FAA AD 2005–23–08]. This AD is published * * * in order to control or correct the development of cracks, which could affect the structural integrity of the aircraft. 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 March 31, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • 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: 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; 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–2008–0222; Directorate Identifier 2007–NM–300–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. E:\FR\FM\29FEP1.SGM 29FEP1 11068 Federal Register / Vol. 73, No. 41 / Friday, February 29, 2008 / Proposed Rules We will post all comments we receive, without change, to https:// 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 2007–0150, dated May 22, 2007 [corrected May 23, 2007] (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: rfrederick on PROD1PC67 with PROPOSALS Due to several crack findings in the area of wing centre box lower aft corner at FR47, this area of structure has been subjected to accomplishment of several inspection Service Bulletins [SBs] rendered mandatory in accordance with Airworthiness Limitation Items requirement for A300 aircraft and Airworthiness Directive (AD) F–2004–159 for A300–600 aircraft [which corresponds to FAA AD 2005–23–08]. This AD is published in order to render mandatory inspection subsequent to accomplishment of repair SB A300–53–0282 or A300[–53]–0291 or A300– 57–6069 in the affected area. The SB A300– 53–0381, A300–53–0383 and A300–57–6102 define the various configurations for the mandatory [repetitive] inspections to be conducted in order to control or correct the development of cracks [in the center wing box at FR47], which could affect the structural integrity of the aircraft. The inspections include x-ray, high frequency eddy current, visual, and ultrasonic inspections. Corrective actions include contacting Airbus if any cracking is found, repairing if any cracking is found, and doing other specified actions. The other specified actions include contacting Airbus for oversizing fastener holes, oversizing fastener holes, installing new fasteners, and installing new plugs. The initial compliance times range from 10,800 flight hours or 23,300 flight cycles, whichever occurs first, to 30,200 flight hours or 33,500 flight cycles, whichever occurs first, after doing the repair, depending on the airplane configuration and inspection area. The repetitive intervals range from 500 flight cycles or 1,100 flight cycles, whichever occurs first, to 45,500 flight cycles or 61,500 flight hours, whichever occurs first, depending on the airplane configuration and inspection area. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletins A300–53–0381, dated January 15, 2007; VerDate Aug<31>2005 15:34 Feb 28, 2008 Jkt 214001 A300–53–0383, dated January 11, 2007; and A300–57–6102, dated January 12, 2007. 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 107 products of U.S. registry. We also estimate that it would take about 22 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 $188,320, or $1,760 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: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 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, 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–2008–0222; Directorate Identifier 2007–NM–300–AD. Comments Due Date (a) We must receive comments by March 31, 2008. Affected ADs (b) None. E:\FR\FM\29FEP1.SGM 29FEP1 Federal Register / Vol. 73, No. 41 / Friday, February 29, 2008 / Proposed Rules Applicability (c) This AD applies to Airbus Model A300 and A300–600 series airplanes, certificated in any category, as listed in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Airbus Model A300 B2–1C, B2–203 and B2K–3C models, all serial numbers that have been repaired in accordance with Airbus Service Bulletin A300–53–0282. (2) Airbus Model A300 B4–103, B4–203, and B4–2C, all serial numbers that have been repaired in accordance with Airbus Service Bulletin A300–53–0291. (3) Airbus Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, B4–622R, C4– 605R Variant F, and F4–605R models, all serial numbers that have been repaired in accordance with Airbus Service Bulletin A300–57–6069. Subject (d) Air Transport Association (ATA) of America Codes 53 and 57: Fuselage and Wings. rfrederick on PROD1PC67 with PROPOSALS Reason (e) The mandatory continuing airworthiness information (MCAI) states: Due to several crack findings in the area of wing centre box lower aft corner at FR47, this area of structure has been subjected to accomplishment of several inspection Service Bulletins [SBs] rendered mandatory in accordance with Airworthiness Limitation Items requirement for A300 aircraft and Airworthiness Directive (AD) F–2004–159 for A300–600 aircraft [which corresponds to FAA AD 2005–23–08]. This AD is published in order to render mandatory an inspection subsequent to accomplishment of repair SB A300–53–0282 or A300[–53]–0291 or A300– 57–6069 in the affected area. The SB A300– 53–0381, A300–53–0383 and A300–57–6102 define the various configurations for the mandatory [repetitive] inspections to be conducted in order to control or correct the development of cracks [in the center wing box at FR47], which could affect the structural integrity of the aircraft. The inspections include x-ray, high frequency eddy current, visual, and ultrasonic inspections. Corrective actions include contacting Airbus if any cracking is found, repairing if any cracking is found, and doing other specified actions. The other specified actions include contacting Airbus for oversizing fastener holes, oversizing fastener holes, installing new fasteners, and installing new plugs. Actions and Compliance (f) Unless already done, do the following actions. (1) Except as provided by paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), (f)(1)(iv), and (f)(1)(v) of this AD, at the threshold defined in paragraph 1.E. ‘‘Compliance’’ of the applicable service bulletin listed in Table 1 of this AD and according to the Accomplishment Instructions of the applicable service bulletin, perform all applicable inspections and, before further flight, perform all applicable other specified actions, of FR47 forward fitting vertical splice (including crack stop hole), crack stop hole (depending on cracks length and VerDate Aug<31>2005 15:34 Feb 28, 2008 Jkt 214001 position), center wing box lower panel, and reinforced parts (internal angle, lower external splice and external fitting). TABLE 1.—AIRBUS SERVICE BULLETINS Service Bulletin A300–53–0381 ............. A300–53–0383 ............. A300–57–6102 ............. Date January 15, 2007. January 11, 2007. January 12, 2007. (i) Where the tables in 1.E. Compliance of the service bulletins listed in Table 1 of this AD contain compliance times in both flight cycles and flight hours, this AD requires that the corresponding actions be done at the earlier of the flight cycle and flight hour compliance times. (ii) Where any table in 1.E. Compliance of the service bulletins listed in Table 1 of this AD specifies measurements for LA and LB and the table does not list the unit of measurements, the unit of measurement is millimeters (mm). (iii) Where any table in 1.E. Compliance of the service bulletins listed in Table 1 of this AD specifies exact measurements in the rows of the table for LA, use the ranges specified in Table 2 of this AD. TABLE 2.—RANGES FOR LA Where row of the table specifies— Use— LA LA LA LA LA = 0 0 <LA ≤10mm 10mm <LA ≤15mm 15mm <LA ≤20mm = = = = 0 ....................... 10 ..................... 15 ..................... 20 ..................... (iv) Where in 1.E. Compliance of the service bulletins listed in Table 1 of this AD the service bulletins specify a compliance time after receipt of the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. (v) Where any table in 1.E. Compliance of the service bulletins listed in Table 1 of this AD specifies measurements of LA >40mm, this AD requires that the corresponding action be done if LA ≥ to 40mm. (2) If any crack is detected during any inspection required by paragraph (f)(1) of this AD, before further flight, contact Airbus and repair. (3) Repeat the actions specified in paragraph (f)(1) of this AD at the intervals defined in paragraph 1.E. ‘‘Compliance’’ of the applicable service bulletin listed in Table 1 of this AD and according to the Accomplishment Instructions of the applicable service bulletin, except as provided by paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), and (f)(1)(v) of this AD. (4) Within 30 days after doing the inspection required by paragraph (f)(1) of this AD or within 30 days after the effective date of this AD, whichever occurs later, report the first inspection results, whatever they may be, to Airbus as specified in the applicable service bulletin listed in Table 1 of this AD. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 11069 FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: The MCAI and service bulletin did not provide adequate descriptions for certain compliance times. We have clarified the compliance times in paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), (f)(1)(iv), and (f)(1)(v) of this AD. 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, 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: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 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 requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007–0150, dated May 22, 2007 [corrected May 23, 2007], and the Airbus Service Bulletins listed in Table 1 of this AD, for related information. Issued in Renton, Washington, on February 21, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–3823 Filed 2–28–08; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\29FEP1.SGM 29FEP1

Agencies

[Federal Register Volume 73, Number 41 (Friday, February 29, 2008)]
[Proposed Rules]
[Pages 11067-11069]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-3823]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0222; Directorate Identifier 2007-NM-300-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and 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:

    Due to several crack findings in the area of wing centre box 
lower aft corner at FR47, this area of structure has been subjected 
to accomplishment of several inspection Service Bulletins rendered 
mandatory in accordance with Airworthiness Limitation Items 
requirement for A300 aircraft and Airworthiness Directive (AD) F-
2004-159 for A300-600 aircraft [which corresponds to FAA AD 2005-23-
08]. This AD is published * * * in order to control or correct the 
development of cracks, which could affect the structural integrity 
of the aircraft.

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 March 31, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     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: 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
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: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; 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-2008-0222; 
Directorate Identifier 2007-NM-300-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.

[[Page 11068]]

    We will post all comments we receive, without change, to https://
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 2007-0150, dated May 22, 2007 [corrected May 
23, 2007] (referred to after this as ``the MCAI''), to correct an 
unsafe condition for the specified products. The MCAI states:

    Due to several crack findings in the area of wing centre box 
lower aft corner at FR47, this area of structure has been subjected 
to accomplishment of several inspection Service Bulletins [SBs] 
rendered mandatory in accordance with Airworthiness Limitation Items 
requirement for A300 aircraft and Airworthiness Directive (AD) F-
2004-159 for A300-600 aircraft [which corresponds to FAA AD 2005-23-
08]. This AD is published in order to render mandatory inspection 
subsequent to accomplishment of repair SB A300-53-0282 or A300[-53]-
0291 or A300-57-6069 in the affected area. The SB A300-53-0381, 
A300-53-0383 and A300-57-6102 define the various configurations for 
the mandatory [repetitive] inspections to be conducted in order to 
control or correct the development of cracks [in the center wing box 
at FR47], which could affect the structural integrity of the 
aircraft.

The inspections include x-ray, high frequency eddy current, visual, and 
ultrasonic inspections. Corrective actions include contacting Airbus if 
any cracking is found, repairing if any cracking is found, and doing 
other specified actions. The other specified actions include contacting 
Airbus for oversizing fastener holes, oversizing fastener holes, 
installing new fasteners, and installing new plugs.

    The initial compliance times range from 10,800 flight hours or 
23,300 flight cycles, whichever occurs first, to 30,200 flight hours or 
33,500 flight cycles, whichever occurs first, after doing the repair, 
depending on the airplane configuration and inspection area. The 
repetitive intervals range from 500 flight cycles or 1,100 flight 
cycles, whichever occurs first, to 45,500 flight cycles or 61,500 
flight hours, whichever occurs first, depending on the airplane 
configuration and inspection area. You may obtain further information 
by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletins A300-53-0381, dated January 15, 
2007; A300-53-0383, dated January 11, 2007; and A300-57-6102, dated 
January 12, 2007. 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 107 products of U.S. registry. We also estimate that 
it would take about 22 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 $188,320, or $1,760 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, 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-2008-0222; Directorate Identifier 2007-NM-
300-AD.

Comments Due Date

    (a) We must receive comments by March 31, 2008.

Affected ADs

    (b) None.

[[Page 11069]]

Applicability

    (c) This AD applies to Airbus Model A300 and A300-600 series 
airplanes, certificated in any category, as listed in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD.
    (1) Airbus Model A300 B2-1C, B2-203 and B2K-3C models, all 
serial numbers that have been repaired in accordance with Airbus 
Service Bulletin A300-53-0282.
    (2) Airbus Model A300 B4-103, B4-203, and B4-2C, all serial 
numbers that have been repaired in accordance with Airbus Service 
Bulletin A300-53-0291.
    (3) Airbus Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, 
B4-622R, C4-605R Variant F, and F4-605R models, all serial numbers 
that have been repaired in accordance with Airbus Service Bulletin 
A300-57-6069.

Subject

    (d) Air Transport Association (ATA) of America Codes 53 and 57: 
Fuselage and Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Due to several crack findings in the area of wing centre box 
lower aft corner at FR47, this area of structure has been subjected 
to accomplishment of several inspection Service Bulletins [SBs] 
rendered mandatory in accordance with Airworthiness Limitation Items 
requirement for A300 aircraft and Airworthiness Directive (AD) F-
2004-159 for A300-600 aircraft [which corresponds to FAA AD 2005-23-
08]. This AD is published in order to render mandatory an inspection 
subsequent to accomplishment of repair SB A300-53-0282 or A300[-53]-
0291 or A300-57-6069 in the affected area. The SB A300-53-0381, 
A300-53-0383 and A300-57-6102 define the various configurations for 
the mandatory [repetitive] inspections to be conducted in order to 
control or correct the development of cracks [in the center wing box 
at FR47], which could affect the structural integrity of the 
aircraft.

The inspections include x-ray, high frequency eddy current, visual, 
and ultrasonic inspections. Corrective actions include contacting 
Airbus if any cracking is found, repairing if any cracking is found, 
and doing other specified actions. The other specified actions 
include contacting Airbus for oversizing fastener holes, oversizing 
fastener holes, installing new fasteners, and installing new plugs.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Except as provided by paragraphs (f)(1)(i), (f)(1)(ii), 
(f)(1)(iii), (f)(1)(iv), and (f)(1)(v) of this AD, at the threshold 
defined in paragraph 1.E. ``Compliance'' of the applicable service 
bulletin listed in Table 1 of this AD and according to the 
Accomplishment Instructions of the applicable service bulletin, 
perform all applicable inspections and, before further flight, 
perform all applicable other specified actions, of FR47 forward 
fitting vertical splice (including crack stop hole), crack stop hole 
(depending on cracks length and position), center wing box lower 
panel, and reinforced parts (internal angle, lower external splice 
and external fitting).

                   Table 1.--Airbus Service Bulletins
------------------------------------------------------------------------
           Service Bulletin                           Date
------------------------------------------------------------------------
A300-53-0381.........................  January 15, 2007.
A300-53-0383.........................  January 11, 2007.
A300-57-6102.........................  January 12, 2007.
------------------------------------------------------------------------

    (i) Where the tables in 1.E. Compliance of the service bulletins 
listed in Table 1 of this AD contain compliance times in both flight 
cycles and flight hours, this AD requires that the corresponding 
actions be done at the earlier of the flight cycle and flight hour 
compliance times.
    (ii) Where any table in 1.E. Compliance of the service bulletins 
listed in Table 1 of this AD specifies measurements for LA and LB 
and the table does not list the unit of measurements, the unit of 
measurement is millimeters (mm).
    (iii) Where any table in 1.E. Compliance of the service 
bulletins listed in Table 1 of this AD specifies exact measurements 
in the rows of the table for LA, use the ranges specified in Table 2 
of this AD.

                         Table 2.--Ranges for LA
------------------------------------------------------------------------
    Where row of the table specifies--                  Use--
------------------------------------------------------------------------
LA = 0....................................  LA = 0
LA = 10...................................  0 40mm, 
this AD requires that the corresponding action be done if LA >= to 
40mm.
    (2) If any crack is detected during any inspection required by 
paragraph (f)(1) of this AD, before further flight, contact Airbus 
and repair.
    (3) Repeat the actions specified in paragraph (f)(1) of this AD 
at the intervals defined in paragraph 1.E. ``Compliance'' of the 
applicable service bulletin listed in Table 1 of this AD and 
according to the Accomplishment Instructions of the applicable 
service bulletin, except as provided by paragraphs (f)(1)(i), 
(f)(1)(ii), (f)(1)(iii), and (f)(1)(v) of this AD.
    (4) Within 30 days after doing the inspection required by 
paragraph (f)(1) of this AD or within 30 days after the effective 
date of this AD, whichever occurs later, report the first inspection 
results, whatever they may be, to Airbus as specified in the 
applicable service bulletin listed in Table 1 of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: The MCAI and service bulletin did not provide adequate 
descriptions for certain compliance times. We have clarified the 
compliance times in paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), 
(f)(1)(iv), and (f)(1)(v) of this AD.

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, 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: Tom 
Stafford, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 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 requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI EASA Airworthiness Directive 2007-0150, dated 
May 22, 2007 [corrected May 23, 2007], and the Airbus Service 
Bulletins listed in Table 1 of this AD, for related information.

    Issued in Renton, Washington, on February 21, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-3823 Filed 2-28-08; 8:45 am]
BILLING CODE 4910-13-P

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