Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4-600R Series Airplanes, Model A300 F4-605R Airplanes, and Model A300 C4-605R Variant F Airplanes, 6549-6551 [2011-2433]

Download as PDF Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0801; Directorate Identifier 2010–NM–054–AD; Amendment 39–16595; AD 2011–03–11] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600 and A300 B4–600R Series Airplanes, Model A300 F4–605R Airplanes, and Model A300 C4–605R Variant F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: A recent Wide spread Fatigue Damage (WFD) calculation on A300–600 aeroplanes has shown that a reinforcement of the upper fuselage circumferential joint at FR (frame) 58 is necessary to enable the aeroplane to reach the Extended Service Goal (ESG). The failure of the circumferential joint of the upper fuselage could affect the structural integrity of the aeroplane. wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective March 14, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 14, 2011. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: VerDate Mar<15>2010 14:36 Feb 04, 2011 Jkt 223001 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on August 23, 2010 (75 FR 51705). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: A recent Wide spread Fatigue Damage (WFD) calculation on A300–600 aeroplanes has shown that a reinforcement of the upper fuselage circumferential joint at FR (frame) 58 is necessary to enable the aeroplane to reach the Extended Service Goal (ESG). The failure of the circumferential joint of the upper fuselage could affect the structural integrity of the aeroplane. For the reasons described above, this AD requires the reinforcement of the affected fuselage frame butt joint. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Revise Paragraph (g) of the NPRM FedEx Express (FedEx) requested that we add the following sentence to paragraph (g) of the NPRM: ‘‘Accomplish modification in accordance with the thresholds specified in [Airbus Mandatory] Service Bulletin A300–53–6146, Revision 01, [dated June 26, 2009,] paragraph E(2), Accomplishment Timescale.’’ FedEx stated that the threshold table in that service bulletin recommends the number of flight cycles for each model after which the modification should be embodied; if the modification is embodied before the recommended threshold, additional inspections are required according to Airbus instructions. FedEx further stated that the NPRM stipulates accomplishment before 42,500 flight cycles and FedEx agrees that following the Airbus recommendation for the thresholds will avoid extensive inspections similar to the Airworthiness Limitations Items (ALI) Tasks 53.16.04–01–1 and 53.16.22–01–1. We do not agree to add the quoted sentence to the AD because, by doing the requirements of this AD at or before the compliance time specified in this AD, no further inspections are required by this AD. However, we have added a new Note 1 that states ‘‘In case of earlier accomplishment of Airbus Mandatory Service Bulletin A300–53–6146, Revision 01, dated June 26, 2009, before PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 6549 the recommended thresholds contained in the Threshold Table in paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A300–53–6146, Revision 01, dated June 26, 2009, are reached, the operator should contact Airbus to define an additional non-mandatory appropriate inspection program.’’ We have reidentified subsequent notes accordingly. Further, we have determined that accomplishing the actions required by this AD terminates ALI Tasks 53.16.04– 01–1 and 53.16.22–01–1. Therefore, we have added a new paragraph (h) to this AD to clarify that doing the requirements of this AD terminates ALI Tasks 53.16.04–01–1 and 53.16.22–01– 1. We have reidentified subsequent paragraphs accordingly. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a Note within the AD. Costs of Compliance We estimate that this AD will affect about 124 products of U.S. registry. We also estimate that it will take about 347 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $5,670 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 parts. 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 E:\FR\FM\07FER1.SGM 07FER1 6550 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations this AD to the U.S. operators to be $4,360,460 or $35,165 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 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 AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2011–03–11 Airbus: Amendment 39–16595. Docket No. FAA–2010–0801; Directorate Identifier 2010–NM–054–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 14, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4– 622R airplanes; Model A300 F4–605R airplanes on which modification 12699 has not been accomplished; and Model A300 C4– 605R Variant F airplanes; certificated in any category; all serial numbers. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: A recent Wide spread Fatigue Damage (WFD) calculation on A300–600 aeroplanes has shown that a reinforcement of the upper fuselage circumferential joint at FR (frame) 58 is necessary to enable the aeroplane to reach the Extended Service Goal (ESG). The failure of the circumferential joint of the upper fuselage could affect the structural integrity of the aeroplane. wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 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 the NPRM, 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. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. VerDate Mar<15>2010 14:36 Feb 04, 2011 Jkt 223001 * * * * Actions (g) Before the accumulation of 42,500 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later, reinforce the fuselage butt joint at FR 58 in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–6146, PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Revision 01, including Appendix 1, dated June 26, 2009. (h) Accomplishment of the requirements of paragraph (g) of this AD terminates Airworthiness Limitations Items (ALI) Tasks 53.16.04–01–1 and 53.16.22–01–1 for these airplanes. Note 1: In case of earlier accomplishment of Airbus Mandatory Service Bulletin A300– 53–6146, Revision 01, dated June 26, 2009, before the recommended thresholds contained in the Threshold Table in paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A300–53–6146, Revision 01, dated June 26, 2009, are reached, the operator should contact Airbus to define an additional appropriate inspection program. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (i) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (j) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0007, dated January 7, 2010; and Airbus Mandatory Service Bulletin A300–53– 6146, Revision 01, including Appendix 1, dated June 26, 2009; for related information. Material Incorporated by Reference (k) You must use Airbus Mandatory Service Bulletin A300–53–6146, Revision 01, including Appendix 1, dated June 26, 2009, to do the actions required by this AD, unless the AD specifies otherwise. E:\FR\FM\07FER1.SGM 07FER1 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail account.airwortheas@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on January 25, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–2433 Filed 2–4–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 878 [Docket No. FDA–2010–D–0645] Medical Devices; General and Plastic Surgery Devices; Classification of Contact Cooling System for Aesthetic Use AGENCY: Food and Drug Administration, HHS. ACTION: Final rule. The Food and Drug Administration (FDA) is classifying the contact cooling system for aesthetic use into class II (special controls). The special control that will apply to the device is the guidance document entitled ‘‘Guidance for Industry and FDA Staff; Class II Special Controls Guidance Document: Contact Cooling System for Aesthetic Use.’’ The Agency is classifying the device into class II (special controls) in order to provide reasonable assurance of safety and effectiveness of the device. Elsewhere in this issue of the Federal Register, FDA is announcing the availability of a guidance document that will serve as the special control for this device type. wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 SUMMARY: VerDate Mar<15>2010 14:36 Feb 04, 2011 Jkt 223001 DATES: Effective Date: March 9, 2011. FOR FURTHER INFORMATION CONTACT: Richard Felten, Center for Devices and Radiological Health, Food and Drug Administration, 10903 New Hampshire Ave., Bldg. 66, rm. 1436, Silver Spring, MD 20993, 301–796–6392. SUPPLEMENTARY INFORMATION: I. What is the background of this rulemaking? The Federal Food, Drug, and Cosmetic Act (the FD&C Act) (21 U.S.C. 301 et seq.) as amended by the Medical Device Amendments of 1976 (the 1976 amendments) (Pub. L. 94–295), the Safe Medical Devices Act of 1990 (Pub. L. 101–629), and the Food and Drug Administration Modernization Act (Pub. L. 107–250) established a comprehensive system for regulation of medical devices intended for human use. Section 513 of the FD&C Act (21 U.S.C. 360c) established three categories (classes) of devices, depending on the regulatory controls needed to provide reasonable assurance of their safety and effectiveness. The three categories of devices are class I (general controls), class II (special controls), and class III (premarket approval). FDA refers to devices that were not in commercial distribution before May 28, 1976 (the date of enactment of the 1976 amendments), as postamendments devices. Postamendments devices are classified automatically by statute (section 513(f) of the FD&C Act) into class III without any FDA rulemaking process. These devices remain in class III and require premarket approval unless: (1) FDA reclassifies the device into class I or II; (2) FDA issues an order classifying the device into class I or class II in accordance with section 513(f)(2) of the FD&C Act; or FDA issues an order finding the device to be substantially equivalent, under section 513(i) to a predicate device that does not require premarket approval. The Agency determines whether new devices are substantially equivalent to predicate devices by means of premarket notification procedures in section 510(k) of FD&C Act (21 U.S.C. 360(k)) and 21 CFR part 807 of the regulations. Section 513(f)(2) of the FD&C Act provides that any person who submits a premarket notification under section 510(k) of the FD&C Act for a device that has not previously been classified may, within 30 days after receiving an order classifying the device that has not previously been classified into class III under section 513(f)(1), request FDA to classify the device under the criteria set forth in section 513(a)(1). FDA will, within 60 days of receiving this request, PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 6551 classify the device by written order. This classification shall be the initial classification of the device. Within 30 days after the issuance of an order classifying the device, FDA must publish a notice in the Federal Register announcing this classification. In accordance with section 513(f)(1) of the FD&C Act, FDA issued an order on October 7, 2009, classifying the Zeltiq Lipolysis System for Aesthetic Use into class III, because it was not substantially equivalent to a device that was introduced or delivered for introduction into interstate commerce for commercial distribution before May 28, 1976, or a device which was subsequently reclassified into class I or class II. On October 13, 2009, ZeltiqTM Aesthetic, Inc., submitted a petition requesting classification of the lipolysis system for aesthetic use under section 513(f)(2) of the FD&C Act. The manufacturer recommended that the device be classified into class II (Ref. 1). In accordance with section 513(f)(2) of the FD&C Act, FDA reviewed the petition in order to classify the device under the criteria for classification set forth in section 513(a)(1). FDA classifies devices into class II if general controls by themselves are insufficient information to establish special controls to provide reasonable assurance of the safety and effectiveness of the device for its intended use. After review of the information submitted in the petition, FDA determined that the contact cooling system for aesthetic use can be classified into class II with the establishment of special controls. FDA believes these special controls will provide assurance of the safety and effectiveness of the device. The device was assigned the generic name ‘‘Cooling System for Aesthetic Use’’ and it is identified as a cooling system for aesthetic use. FDA has identified the following risks to health associated specifically with this type of device and the recommended measures to mitigate these risks. • Discomfort and pain during and following treatment are possible due to the application of mechanical or vacuum massage at levels in excess of those recommended in the labeling. These effects and tenderness at the treatment site may also occur following treatment. Prevention of these effects are addressed by adequate bench testing demonstrating that the feedback controls for temperature/cooling are functional and do maintain target temperature within the stated value. Proper function of mechanical controls to insure use of the mechanical or vacuum massager within safe limits E:\FR\FM\07FER1.SGM 07FER1

Agencies

[Federal Register Volume 76, Number 25 (Monday, February 7, 2011)]
[Rules and Regulations]
[Pages 6549-6551]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-2433]



[[Page 6549]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0801; Directorate Identifier 2010-NM-054-AD; 
Amendment 39-16595; AD 2011-03-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4-
600R Series Airplanes, Model A300 F4-605R Airplanes, and Model A300 C4-
605R Variant F Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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:

    A recent Wide spread Fatigue Damage (WFD) calculation on A300-
600 aeroplanes has shown that a reinforcement of the upper fuselage 
circumferential joint at FR (frame) 58 is necessary to enable the 
aeroplane to reach the Extended Service Goal (ESG).
    The failure of the circumferential joint of the upper fuselage 
could affect the structural integrity of the aeroplane.
* * * * *
    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective March 14, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 14, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on August 23, 2010 (75 
FR 51705). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    A recent Wide spread Fatigue Damage (WFD) calculation on A300-
600 aeroplanes has shown that a reinforcement of the upper fuselage 
circumferential joint at FR (frame) 58 is necessary to enable the 
aeroplane to reach the Extended Service Goal (ESG).
    The failure of the circumferential joint of the upper fuselage 
could affect the structural integrity of the aeroplane.
    For the reasons described above, this AD requires the 
reinforcement of the affected fuselage frame butt joint.

    You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Revise Paragraph (g) of the NPRM

    FedEx Express (FedEx) requested that we add the following sentence 
to paragraph (g) of the NPRM: ``Accomplish modification in accordance 
with the thresholds specified in [Airbus Mandatory] Service Bulletin 
A300-53-6146, Revision 01, [dated June 26, 2009,] paragraph E(2), 
Accomplishment Timescale.'' FedEx stated that the threshold table in 
that service bulletin recommends the number of flight cycles for each 
model after which the modification should be embodied; if the 
modification is embodied before the recommended threshold, additional 
inspections are required according to Airbus instructions. FedEx 
further stated that the NPRM stipulates accomplishment before 42,500 
flight cycles and FedEx agrees that following the Airbus recommendation 
for the thresholds will avoid extensive inspections similar to the 
Airworthiness Limitations Items (ALI) Tasks 53.16.04-01-1 and 53.16.22-
01-1.
    We do not agree to add the quoted sentence to the AD because, by 
doing the requirements of this AD at or before the compliance time 
specified in this AD, no further inspections are required by this AD. 
However, we have added a new Note 1 that states ``In case of earlier 
accomplishment of Airbus Mandatory Service Bulletin A300-53-6146, 
Revision 01, dated June 26, 2009, before the recommended thresholds 
contained in the Threshold Table in paragraph 1.E.(2) of Airbus 
Mandatory Service Bulletin A300-53-6146, Revision 01, dated June 26, 
2009, are reached, the operator should contact Airbus to define an 
additional non-mandatory appropriate inspection program.'' We have 
reidentified subsequent notes accordingly.
    Further, we have determined that accomplishing the actions required 
by this AD terminates ALI Tasks 53.16.04-01-1 and 53.16.22-01-1. 
Therefore, we have added a new paragraph (h) to this AD to clarify that 
doing the requirements of this AD terminates ALI Tasks 53.16.04-01-1 
and 53.16.22-01-1. We have reidentified subsequent paragraphs 
accordingly.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect about 124 products of U.S. 
registry. We also estimate that it will take about 347 work-hours per 
product to comply with the basic requirements of this AD. The average 
labor rate is $85 per work-hour. Required parts will cost about $5,670 
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 parts. 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

[[Page 6550]]

this AD to the U.S. operators to be $4,360,460 or $35,165 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    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 AD and placed it in the AD docket.

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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2011-03-11 Airbus: Amendment 39-16595. Docket No. FAA-2010-0801; 
Directorate Identifier 2010-NM-054-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
14, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; 
Model A300 F4-605R airplanes on which modification 12699 has not 
been accomplished; and Model A300 C4-605R Variant F airplanes; 
certificated in any category; all serial numbers.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    A recent Wide spread Fatigue Damage (WFD) calculation on A300-
600 aeroplanes has shown that a reinforcement of the upper fuselage 
circumferential joint at FR (frame) 58 is necessary to enable the 
aeroplane to reach the Extended Service Goal (ESG).
    The failure of the circumferential joint of the upper fuselage 
could affect the structural integrity of the aeroplane.
* * * * *

Compliance

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

Actions

    (g) Before the accumulation of 42,500 total flight cycles, or 
within 2,000 flight cycles after the effective date of this AD, 
whichever occurs later, reinforce the fuselage butt joint at FR 58 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-53-6146, Revision 01, including 
Appendix 1, dated June 26, 2009.
    (h) Accomplishment of the requirements of paragraph (g) of this 
AD terminates Airworthiness Limitations Items (ALI) Tasks 53.16.04-
01-1 and 53.16.22-01-1 for these airplanes.

    Note 1:  In case of earlier accomplishment of Airbus Mandatory 
Service Bulletin A300-53-6146, Revision 01, dated June 26, 2009, 
before the recommended thresholds contained in the Threshold Table 
in paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A300-53-
6146, Revision 01, dated June 26, 2009, are reached, the operator 
should contact Airbus to define an additional appropriate inspection 
program.

FAA AD Differences

    Note 2:  This AD differs from the MCAI and/or service 
information as follows:
    No differences.

Other FAA AD Provisions

    (i) 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: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before 
using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (j) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2010-0007, dated January 7, 2010; and Airbus 
Mandatory Service Bulletin A300-53-6146, Revision 01, including 
Appendix 1, dated June 26, 2009; for related information.

Material Incorporated by Reference

    (k) You must use Airbus Mandatory Service Bulletin A300-53-6146, 
Revision 01, including Appendix 1, dated June 26, 2009, to do the 
actions required by this AD, unless the AD specifies otherwise.

[[Page 6551]]

    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com; 
Internet https://www.airbus.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on January 25, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-2433 Filed 2-4-11; 8:45 am]
BILLING CODE 4910-13-P
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