Airworthiness Directives; Airbus Model A310-304, -322, -324, and -325 Airplanes; and A300 Model B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, F4-605R, F4-622R, and C4-605R Variant F Airplanes (Commonly Called Model A300-600 Series Airplanes), 71832-71834 [E7-24523]

Download as PDF 71832 Federal Register / Vol. 72, No. 243 / Wednesday, December 19, 2007 / Proposed Rules for this AD, follow the procedures in 14 CFR 39.19. 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. Issued in Renton, Washington, on December 10, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–24521 Filed 12–18–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0345; Directorate Identifier 2007–NM–194–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310–304, –322, –324, and –325 Airplanes; and A300 Model B4–601, B4–603, B4–605R, B4–620, B4–622, B4–622R, F4–605R, F4–622R, and C4– 605R Variant F Airplanes (Commonly Called 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: rwilkins on PROD1PC63 with PROPOSALS Due to the recalculation of loads for the Multi Role Transporter and Tanker (MRTT) aircraft, it has been found that a structural reinforcement at the aft section of the fuselage (FR (frame) 87–FR91) is required for A300–600 aircraft and A310 aircraft with a Trim Tank installed. * * * The unsafe condition is the potential loss of structural integrity in the aft section of the fuselage between FR87 through FR91, inclusive, during extreme rolling and vertical maneuver combinations. 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 January 18, 2008. ADDRESSES: You may send comments by any of the following methods: VerDate Aug<31>2005 19:24 Dec 18, 2007 Jkt 214001 • Federal eRulemaking Portal: Go to http://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 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: 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–2007–0345; Directorate Identifier 2007–NM–194–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 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Airworthiness Directive 2007–0173, dated June 18, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Due to the recalculation of loads for the Multi Role Transporter and Tanker (MRTT) aircraft, it has been found that a structural reinforcement at the aft section of the fuselage (FR (frame) 87–FR91) is required for A300–600 aircraft and A310 aircraft with a Trim Tank installed. * * * The unsafe condition is the potential loss of structural integrity in the aft section of the fuselage between FR87 through FR91, inclusive, during extreme rolling and vertical maneuver combinations. The corrective action is reinforcing the structure at FR91. Related investigative and corrective actions (reinforcement) include: • Doing a rotating probe inspection for cracking of the fastener holes; • Reaming the fastener holes; and • Contacting Airbus for repair instructions and repairing any crack found in any reamed fastener hole. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletins A310–53–2126 and A300–53–6156, both dated November 28, 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 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. E:\FR\FM\19DEP1.SGM 19DEP1 Federal Register / Vol. 72, No. 243 / Wednesday, December 19, 2007 / Proposed Rules 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 160 products of U.S. registry. We also estimate that it would take about 129 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $5,840 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 $2,585,600, or $16,160 per product. rwilkins on PROD1PC63 with PROPOSALS 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; VerDate Aug<31>2005 19:24 Dec 18, 2007 Jkt 214001 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–2007–0345; Directorate Identifier 2007–NM–194–AD. Comments Due Date (a) We must receive comments by January 18, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A310– 304, –322, –324, and –325 airplanes, certificated in any category, all serial numbers, except those which have received in service application of Airbus Service Bulletin A310–53–2126 (Airbus modification No. 13011). This AD also applies to Airbus A300 Model B4–601, B4–603, B4–605R, B4– 620, B4–622, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes (commonly called Model A300–600 series airplanes), certificated in any category, all serial numbers, except those which have received application of Airbus modification No. 13273 in production or application of Airbus Service Bulletin A300–53–6156 in service. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Due to the recalculation of loads for the Multi Role Transporter and Tanker (MRTT) aircraft, it has been found that a structural reinforcement at the aft section of the fuselage (FR (frame) 87–FR91) is required for PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 71833 A300–600 aircraft and A310 aircraft with a Trim Tank installed. * * * The unsafe condition is the potential loss of structural integrity in the aft section of the fuselage between FR87 through FR91, inclusive, during extreme rolling and vertical maneuver combinations. The corrective action is reinforcing the structure at FR91. Related investigative and corrective actions (reinforcement) include: Doing a rotating probe inspection for cracking of the fastener holes; reaming the fastener holes; and contacting Airbus for repair instructions and repairing any crack found in any reamed fastener hole. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 2,500 flight cycles after the effective date of this AD, reinforce the aft section of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–53–2126 or Service Bulletin A300–53–6156, as applicable, both dated November 28, 2006. Do all related and investigative corrective actions, as applicable, before further flight. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No difference. 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, 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 2007–0173, dated June 18, 2007; Airbus Service Bulletin A310–53–2126, dated November 28, 2006; and Airbus Service Bulletin A300–53–6156, dated November 28, 2006; for related information. E:\FR\FM\19DEP1.SGM 19DEP1 71834 Federal Register / Vol. 72, No. 243 / Wednesday, December 19, 2007 / Proposed Rules Issued in Renton, Washington, on December 10, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–24523 Filed 12–18–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0344; Directorate Identifier 2007–NM–149–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 767–200 and –300 series airplanes. This proposed AD would require replacing the wire segments of the four Fuel Quantity Indicating System (FQIS) wire bundles with new, improved wire segments. This proposed AD results from operator inspections of the FQIS wire bundles that revealed corrosion at the connections between the ground wire and shield of each of the four FQIS wire bundles. We are proposing this AD to prevent this corrosion, which could reduce system protection of the lightning shield and result in loss of the electrical grounding between the lightning shield and the airplane structure. This condition, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. SUMMARY: We must receive comments on this proposed AD by February 4, 2008. 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. • 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 rwilkins on PROD1PC63 with PROPOSALS DATES: VerDate Aug<31>2005 19:24 Dec 18, 2007 Jkt 214001 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility 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 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: Philip Sheridan, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6441; fax (425) 917–6590. 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–2007–0344; Directorate Identifier 2007–NM–149–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 because of those comments. 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 Operator inspections of four Fuel Quantity Indicating System (FQIS) wire bundles revealed corrosion at the connections between the ground wire and shield of each of the four wire bundles, on certain Boeing Model 767– 200 and –300 series airplanes. Corrosion occurred at the ferrules, which were used for connection of the ground wire. The wire bundle shielding is part of the system protection against a lightning PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 strike. The corrosion reduces system protection against a lightning strike. This condition, if not corrected, could result in loss of the electrical grounding between the lightning shield and the airplane structure. Loss of the electrical grounding between the lightning shield and the airplane structure, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 767–28A0064, Revision 2, dated October 27, 2005. The service bulletin describes procedures for replacing the wire segments of the four FQIS wire bundles with new, improved wire segments. The service bulletin also describes procedures for an operational test of the FQIS following the replacement. Accomplishing the actions specified in the service bulletin is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service bulletin described previously, except as discussed under ‘‘Difference Between the Proposed AD and Service Bulletin.’’ Difference Between the Proposed AD and Service Bulletin The service bulletin recommends accomplishing the replacement of the wire segments of the four FQIS wire bundles within 48 months after the release date of the service bulletin, but we have determined that this compliance time would not address the identified unsafe condition in a timely manner. In developing an appropriate compliance time for this AD, we considered not only the manufacturer’s recommendation, but the degree of urgency associated with addressing the subject unsafe condition, the average utilization of the affected fleet, and the time necessary to perform the replacement. In light of all of these factors, we find a compliance time of 36 months after the effective date of the AD for completing the required replacement to be warranted, in that it represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. This difference has been coordinated with Boeing. E:\FR\FM\19DEP1.SGM 19DEP1

Agencies

[Federal Register Volume 72, Number 243 (Wednesday, December 19, 2007)]
[Proposed Rules]
[Pages 71832-71834]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-24523]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0345; Directorate Identifier 2007-NM-194-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-304, -322, -324, and 
-325 Airplanes; and A300 Model B4-601, B4-603, B4-605R, B4-620, B4-622, 
B4-622R, F4-605R, F4-622R, and C4-605R Variant F Airplanes (Commonly 
Called 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:

    Due to the recalculation of loads for the Multi Role Transporter 
and Tanker (MRTT) aircraft, it has been found that a structural 
reinforcement at the aft section of the fuselage (FR (frame) 87-
FR91) is required for A300-600 aircraft and A310 aircraft with a 
Trim Tank installed. * * *

The unsafe condition is the potential loss of structural integrity in 
the aft section of the fuselage between FR87 through FR91, inclusive, 
during extreme rolling and vertical maneuver combinations. 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 January 18, 
2008.

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.
     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 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: 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-2007-0345; 
Directorate Identifier 2007-NM-194-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 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 2007-0173, dated June 18, 2007 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Due to the recalculation of loads for the Multi Role Transporter 
and Tanker (MRTT) aircraft, it has been found that a structural 
reinforcement at the aft section of the fuselage (FR (frame) 87-
FR91) is required for A300-600 aircraft and A310 aircraft with a 
Trim Tank installed. * * *

The unsafe condition is the potential loss of structural integrity in 
the aft section of the fuselage between FR87 through FR91, inclusive, 
during extreme rolling and vertical maneuver combinations. The 
corrective action is reinforcing the structure at FR91. Related 
investigative and corrective actions (reinforcement) include:
     Doing a rotating probe inspection for cracking of the 
fastener holes;
     Reaming the fastener holes; and
     Contacting Airbus for repair instructions and repairing 
any crack found in any reamed fastener hole.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued Service Bulletins A310-53-2126 and A300-53-6156, 
both dated November 28, 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 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.

[[Page 71833]]

    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 160 products of U.S. registry. We also estimate that 
it would take about 129 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Required parts would cost about $5,840 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 $2,585,600, or $16,160 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-2007-0345; Directorate Identifier 2007-NM-
194-AD.

Comments Due Date

    (a) We must receive comments by January 18, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-304, -322, -324, and -
325 airplanes, certificated in any category, all serial numbers, 
except those which have received in service application of Airbus 
Service Bulletin A310-53-2126 (Airbus modification No. 13011). This 
AD also applies to Airbus A300 Model B4-601, B4-603, B4-605R, B4-
620, B4-622, B4-622R, F4-605R, F4-622R, and C4-605R Variant F 
airplanes (commonly called Model A300-600 series airplanes), 
certificated in any category, all serial numbers, except those which 
have received application of Airbus modification No. 13273 in 
production or application of Airbus Service Bulletin A300-53-6156 in 
service.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Due to the recalculation of loads for the Multi Role Transporter 
and Tanker (MRTT) aircraft, it has been found that a structural 
reinforcement at the aft section of the fuselage (FR (frame) 87-
FR91) is required for A300-600 aircraft and A310 aircraft with a 
Trim Tank installed. * * *
    The unsafe condition is the potential loss of structural 
integrity in the aft section of the fuselage between FR87 through 
FR91, inclusive, during extreme rolling and vertical maneuver 
combinations. The corrective action is reinforcing the structure at 
FR91. Related investigative and corrective actions (reinforcement) 
include: Doing a rotating probe inspection for cracking of the 
fastener holes; reaming the fastener holes; and contacting Airbus 
for repair instructions and repairing any crack found in any reamed 
fastener hole.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 2,500 flight cycles after the effective date of this 
AD, reinforce the aft section of the fuselage, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A310-53-
2126 or Service Bulletin A300-53-6156, as applicable, both dated 
November 28, 2006. Do all related and investigative corrective 
actions, as applicable, before further flight.

FAA AD Differences

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

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, 
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 2007-0173, dated 
June 18, 2007; Airbus Service Bulletin A310-53-2126, dated November 
28, 2006; and Airbus Service Bulletin A300-53-6156, dated November 
28, 2006; for related information.


[[Page 71834]]


    Issued in Renton, Washington, on December 10, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-24523 Filed 12-18-07; 8:45 am]
BILLING CODE 4910-13-P