Airworthiness Directives; Airbus Model A300 Series Airplanes, 29449-29451 [E7-10218]

Download as PDF Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have 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 that the 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. See the ADDRESSES section for a location to examine the regulatory evaluation. 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] rwilkins on PROD1PC63 with PROPOSALS 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas: Docket No. FAA–2007– 28301; Directorate Identifier 2007–NM– 061–AD. Comments Due Date (a) The FAA must receive comments on this AD action by July 13, 2007. Affected ADs (b) None. VerDate Aug<31>2005 18:04 May 25, 2007 Jkt 211001 Applicability 29449 Issued in Renton, Washington, on May 21, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10215 Filed 5–25–07; 8:45 am] (c) This AD applies to the following McDonnell Douglas airplanes, certificated in any category: (1) All Model MD–11 and MD–11F airplanes. (2) DC–10–10, DC–10–10F, DC–10–15, DC– 10–30 and DC–10–30F (KC–10A and KDC– 10), DC–10–40, DC–10–40F, MD–10–10F, and MD–10–30F airplanes; as identified in Boeing Alert Service Bulletin DC10–29A147, dated February 9, 2007. BILLING CODE 4910–13–P Unsafe Condition 14 CFR Part 39 (d) This AD results from a report of damage to the hydraulic system that occurred when pieces of a ruptured tire from the left main landing gear penetrated the wing trailing edge access panel during takeoff. We are issuing this AD to prevent damage to the system 3 hydraulic piping, which could result in loss of the hydraulic system. [Docket No. FAA–2007–28300; Directorate Identifier 2006–NM–292–AD] Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Modification (f) Within 24 months after the effective date of this AD, reroute system hydraulic piping, install new pipe assemblies and unions, and install redesigned support brackets for system 3 hydraulic piping. Do these actions in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin MD11–29A068, Revision 1, dated February 9, 2007 (for Model MD–11 and MD–11F airplanes), or McDonnell Douglas Service Bulletin DC10– 29A147, dated February 9, 2007 (for Model DC–10–10, DC–10–10F, DC–10–15, DC–10– 30 and DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10–10F, and MD–10–30F airplanes). (g) Accomplishment before the effective date of this AD of the modification required by paragraph (f) of this AD in accordance with McDonnell Douglas Alert Service Bulletin MD11–29A068, dated January 23, 2007, is acceptable for compliance with the requirements of paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 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: The Chromic Acid Anodising (CAA) Lead Fleet Program was established in 1989 to observe corrosion/debonding behaviour of CAA-treated panels. CAA lead fleet includes the inspection of lap joints, circumferential joints, stringers and doublers on selected aircraft. The findings in combination with analytical corrosion investigations have been analysed by the TC (type certificate) holder and an appropriate inspection program for debonding has been developed. This airworthiness directive requires inspection of the concerned areas to detect any corrosion and/or debonding which could affect the structural integrity. * * * 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 June 28, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. E:\FR\FM\29MYP1.SGM 29MYP1 29450 Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. Examining the AD Docket You may examine the AD docket on the Internet at http://dms.dot.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– 5227) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: rwilkins on PROD1PC63 with PROPOSALS Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28300; Directorate Identifier 2006–NM–292–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 VerDate Aug<31>2005 18:04 May 25, 2007 Jkt 211001 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:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. 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. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2006–0369, dated December 12, 2006 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Differences Between This AD and the MCAI or Service Information The Chromic Acid Anodising (CAA) Lead Fleet Program was established in 1989 to observe corrosion/debonding behaviour of CAA-treated panels. CAA lead fleet includes the inspection of lap joints, circumferential joints, stringers and doublers on selected aircraft. The findings in combination with analytical corrosion investigations have been analysed by the TC (type certificate) holder and an appropriate inspection program for debonding has been developed. This airworthiness directive requires inspection of the concerned areas [including repetitive inspections of certain areas] to detect any corrosion and/or debonding which could affect the structural integrity. * * * If any discrepancies are found, repair and follow-up actions (additional inspections for debonding and corrosion depth) are required. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletin A300–53–0378, dated September 4, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. The compliance times for the initial inspections range between 36,800 to 44,600 total flight cycles and between 18 and 20 years since new. The grace period for the initial inspections is 2,000 flight cycles or 2 years, whichever occurs first. The compliance times for the repairs range from before further flight to within 2,000 flight cycles after doing the inspection. The repetitive inspection intervals range from 500 flight cycles to 3 years. 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 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 12 products of U.S. registry. We also estimate that it would take 102 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 $97,920, or $8,160 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. E:\FR\FM\29MYP1.SGM 29MYP1 Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules 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–2007–28300; Directorate Identifier 2006–NM–292–AD. Comments Due Date (a) We must receive comments by June 28, 2007. rwilkins on PROD1PC63 with PROPOSALS Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300 series aircraft, certificated in any category, manufacturing serial numbers (MSN) 0105 through 0107, 0116, 0117, 0121, 0123 through 0126, 0128, 0129, 0133 through 0141, 0146 through 0152, 0154 through 0157, 0160, 0163, 0170, 0173, 0175 through 0177, and 0180 through 0183. Subject (d) Fuselage. VerDate Aug<31>2005 18:04 May 25, 2007 Jkt 211001 Reason (e) The mandatory continuing airworthiness information (MCAI) states: The Chromic Acid Anodising (CAA) Lead Fleet Program was established in 1989 to observe corrosion/debonding behaviour of CAA-treated panels. CAA lead fleet includes the inspection of lap joints, circumferential joints, stringers and doublers on selected aircraft. The findings in combination with analytical corrosion investigations have been analysed by the TC (type certificate) holder and an appropriate inspection program for debonding has been developed. This airworthiness directive requires inspection of the concerned areas [including repetitive inspections of certain areas] to detect any corrosion and/or debonding which could affect the structural integrity. * * * If any discrepancies are found, repair and follow-up actions (additional inspections for debonding and corrosion depth) are required. Actions and Compliance (f) Unless already done, do the following actions. (1) Except as provided by paragraphs (f)(2), (f)(3), and (f)(4) of this AD: Do the initial and repetitive inspections (including follow-up actions), as applicable; and do all applicable repairs; of the areas specified in paragraphs (f)(1)(i), (f)(1)(ii), (f)(1)(iii), and (f)(1)(iv) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0378, dated September 4, 2006, and within the timescales specified in paragraph 1.E.(2), the Accomplishment Instructions, and the figures of the service bulletin. (i) The bonded doubler in the longitudinal lap joint area between frame (FR)18 and FR80 (configurations 01 and 02 inspect FR18 through FR40; configuration 03 inspects FR18 through FR80). (ii) The bonded wing doublers between stringer (STGR)22 LH/RH (left-hand/righthand) and STGR43 LH/RH for debonding (configuration 01 of the service bulletin only). (iii) The bonded doublers in the circumferential joint area between FR26 and FR80 (configurations 01 and 02 inspect FR26 through FR40; configuration 03 inspects FR26 through FR80). (iv) The bonded doublers in the manhole area between FR23 RH and FR24 RH and between FR38.1 RH and FR38.2 RH. (2) Where paragraph 1.E.(2) of Airbus Service Bulletin A300–53–0378, dated September 4, 2006, specifies a grace period ´ from CN (Consigne de Navigabilite) issuance, this AD requires a grace period relative to the effective date of this AD. (3) Where paragraph 1.E.(2) of Airbus Service Bulletin A300–53–0378, dated September 4, 2006, specifies a threshold, this AD requires that the inspections be done within the specified threshold relative to the first flight of the airplane. (4) Where the Accomplishment Instructions and figures of Airbus Service Bulletin A300–53–0378, dated September 4, 2006, specify that inspections be done yearly, this AD requires those inspections to be done at intervals not to exceed 1 year. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 29451 FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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; 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 European Aviation Safety Agency Airworthiness Directive 2006– 0369, dated December 12, 2006; and Airbus Service Bulletin A300–53–0378; dated September 4, 2006, for related information. Issued in Renton, Washington, on May 21, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10218 Filed 5–25–07; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\29MYP1.SGM 29MYP1

Agencies

[Federal Register Volume 72, Number 102 (Tuesday, May 29, 2007)]
[Proposed Rules]
[Pages 29449-29451]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10218]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28300; Directorate Identifier 2006-NM-292-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 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:

    The Chromic Acid Anodising (CAA) Lead Fleet Program was 
established in 1989 to observe corrosion/debonding behaviour of CAA-
treated panels. CAA lead fleet includes the inspection of lap 
joints, circumferential joints, stringers and doublers on selected 
aircraft.
    The findings in combination with analytical corrosion 
investigations have been analysed by the TC (type certificate) 
holder and an appropriate inspection program for debonding has been 
developed.
    This airworthiness directive requires inspection of the 
concerned areas to detect any corrosion and/or debonding which could 
affect the structural integrity. * * *

    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 June 28, 2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to  http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Fax: (202) 493-2251.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.

[[Page 29450]]

     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: http://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
dms.dot.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) 647-5227) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Streamlined Issuance of AD

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

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28300; Directorate Identifier 2006-NM-292-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://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2006-0369, dated December 12, 2006 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    The Chromic Acid Anodising (CAA) Lead Fleet Program was 
established in 1989 to observe corrosion/debonding behaviour of CAA-
treated panels. CAA lead fleet includes the inspection of lap 
joints, circumferential joints, stringers and doublers on selected 
aircraft.
    The findings in combination with analytical corrosion 
investigations have been analysed by the TC (type certificate) 
holder and an appropriate inspection program for debonding has been 
developed.
    This airworthiness directive requires inspection of the 
concerned areas [including repetitive inspections of certain areas] 
to detect any corrosion and/or debonding which could affect the 
structural integrity. * * *

    If any discrepancies are found, repair and follow-up actions 
(additional inspections for debonding and corrosion depth) are 
required. You may obtain further information by examining the MCAI in 
the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A300-53-0378, dated September 4, 
2006. The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI. The compliance 
times for the initial inspections range between 36,800 to 44,600 total 
flight cycles and between 18 and 20 years since new. The grace period 
for the initial inspections is 2,000 flight cycles or 2 years, 
whichever occurs first. The compliance times for the repairs range from 
before further flight to within 2,000 flight cycles after doing the 
inspection. The repetitive inspection intervals range from 500 flight 
cycles to 3 years.

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 12 products of U.S. registry. We also estimate that 
it would take 102 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 $97,920, or $8,160 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.

[[Page 29451]]

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-2007-28300; Directorate Identifier 2006-NM-
292-AD.

Comments Due Date

    (a) We must receive comments by June 28, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 series aircraft, 
certificated in any category, manufacturing serial numbers (MSN) 
0105 through 0107, 0116, 0117, 0121, 0123 through 0126, 0128, 0129, 
0133 through 0141, 0146 through 0152, 0154 through 0157, 0160, 0163, 
0170, 0173, 0175 through 0177, and 0180 through 0183.

Subject

    (d) Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    The Chromic Acid Anodising (CAA) Lead Fleet Program was 
established in 1989 to observe corrosion/debonding behaviour of CAA-
treated panels. CAA lead fleet includes the inspection of lap 
joints, circumferential joints, stringers and doublers on selected 
aircraft.
    The findings in combination with analytical corrosion 
investigations have been analysed by the TC (type certificate) 
holder and an appropriate inspection program for debonding has been 
developed.
    This airworthiness directive requires inspection of the 
concerned areas [including repetitive inspections of certain areas] 
to detect any corrosion and/or debonding which could affect the 
structural integrity. * * *
    If any discrepancies are found, repair and follow-up actions 
(additional inspections for debonding and corrosion depth) are 
required.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Except as provided by paragraphs (f)(2), (f)(3), and (f)(4) 
of this AD: Do the initial and repetitive inspections (including 
follow-up actions), as applicable; and do all applicable repairs; of 
the areas specified in paragraphs (f)(1)(i), (f)(1)(ii), 
(f)(1)(iii), and (f)(1)(iv) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-0378, 
dated September 4, 2006, and within the timescales specified in 
paragraph 1.E.(2), the Accomplishment Instructions, and the figures 
of the service bulletin.
    (i) The bonded doubler in the longitudinal lap joint area 
between frame (FR)18 and FR80 (configurations 01 and 02 inspect FR18 
through FR40; configuration 03 inspects FR18 through FR80).
    (ii) The bonded wing doublers between stringer (STGR)22 LH/RH 
(left-hand/right-hand) and STGR43 LH/RH for debonding (configuration 
01 of the service bulletin only).
    (iii) The bonded doublers in the circumferential joint area 
between FR26 and FR80 (configurations 01 and 02 inspect FR26 through 
FR40; configuration 03 inspects FR26 through FR80).
    (iv) The bonded doublers in the manhole area between FR23 RH and 
FR24 RH and between FR38.1 RH and FR38.2 RH.
    (2) Where paragraph 1.E.(2) of Airbus Service Bulletin A300-53-
0378, dated September 4, 2006, specifies a grace period from CN 
(Consigne de Navigabilit[eacute]) issuance, this AD requires a grace 
period relative to the effective date of this AD.
    (3) Where paragraph 1.E.(2) of Airbus Service Bulletin A300-53-
0378, dated September 4, 2006, specifies a threshold, this AD 
requires that the inspections be done within the specified threshold 
relative to the first flight of the airplane.
    (4) Where the Accomplishment Instructions and figures of Airbus 
Service Bulletin A300-53-0378, dated September 4, 2006, specify that 
inspections be done yearly, this AD requires those inspections to be 
done at intervals not to exceed 1 year.

FAA AD Differences

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

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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; 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 European Aviation Safety Agency Airworthiness 
Directive 2006-0369, dated December 12, 2006; and Airbus Service 
Bulletin A300-53-0378; dated September 4, 2006, for related 
information.

    Issued in Renton, Washington, on May 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-10218 Filed 5-25-07; 8:45 am]
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