Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes, 37477-37479 [E7-13354]

Download as PDF Federal Register / Vol. 72, No. 131 / Tuesday, July 10, 2007 / Proposed Rules possible disruption of the electrical power system due to a lightning strike on a composite drain mast, which could result in the loss of several functions essential for safe flight. Compliance Issued in Renton, Washington, on June 26, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–13353 Filed 7–9–07; 8:45 am] (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. BILLING CODE 4910–13–P Inspection To Determine Material of Gray Water Drain Mast Federal Aviation Administration (f) Within 60 months after the effective date of this AD, inspect the forward and aft gray water drain masts to determine whether the drain mast is made of aluminum or composite material. A review of airplane maintenance records is acceptable in lieu of this inspection if the material of the forward and aft gray water drain masts can be conclusively determined from that review. (1) For any aluminum gray water drain mast identified during the inspection or records check required by paragraph (f) of this AD, no further action is required by this AD for that drain mast only. (2) For any composite gray water drain mast identified during the inspection or records check required by paragraph (f) of this AD, do the actions specified in paragraph (g) of this AD. 14 CFR Part 39 Installation of Bonding Jumper (g) For any composite gray water drain mast identified during the inspection or records check required by paragraph (f) of this AD: Within 60 months after the effective date of this AD, install a 135-ampere copper bonding jumper between a ground and the clamp on the tube of the gray water composite drain mast, in accordance with the Accomplishment instructions of Boeing Special Attention Service Bulletin 777–30– 0014, dated July 24, 2006. rmajette on PROD1PC64 with PROPOSALS Installation of Bonding Jumper Not Necessary for Aluminum Drain Masts (h) For airplanes on which the forward composite drain mast has been replaced with an aluminum drain mast per Boeing Service Bulletin 777–38–0026: Installation of the bonding jumper specified in paragraph (g) of this AD is not required for the forward gray water drain mast, as specified in Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–30– 0014, dated July 24, 2006. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office, 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. VerDate Aug<31>2005 15:19 Jul 09, 2007 Jkt 211001 DEPARTMENT OF TRANSPORTATION [Docket No. FAA–2007–28665; Directorate Identifier 2007–NM–081–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 and A300–600 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Three cases of outer deflector panel found detached or broken during ground inspection have been reported to Airbus. * * * [A]n operator has also reported a missing portion of hinge on one panel. * * * Mishandling or failure of the small portion of hinge located inboard of the affected deflector panel is suspected to be the main cause of the deflector damage. This can cause misalignment of the deflector panel followed by hinge pin migration and possible further damages to the deflector on flap retraction. If not corrected, such situation could lead to the loss of deflector panel and injured people on the ground. 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 August 9, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Room W12–140 on the ground floor of the West Building, PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 37477 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28665; Directorate Identifier 2007–NM–081–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 E:\FR\FM\10JYP1.SGM 10JYP1 37478 Federal Register / Vol. 72, No. 131 / Tuesday, July 10, 2007 / Proposed Rules closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2007–0062, dated March 7, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Three cases of outer deflector panel found detached or broken during ground inspection have been reported by operators to Airbus. The affected deflector panel is the most outboard of the two outer deflectors. In addition, an operator has also reported a missing portion of hinge on one panel. The missing portion of hinge is held to the structure through one Camloc fastener. Mishandling or failure of the small portion of hinge located inboard of the affected deflector panel is suspected to be the main cause of the deflector damage. This can cause misalignment of the deflector panel followed by hinge pin migration and possible further damages to the deflector on flap retraction. If not corrected, such situation could lead to the loss of deflector panel and injured people on the ground. The aim of this Airworthiness Directive (AD) is to mandate the one time inspection to detect and prevent damage to inner and outer shroud box deflectors. The corrective action includes repairing any discrepancy, or removing the affected deflector door according to the Configuration Deviation List (CDL). You may obtain further information by examining the MCAI in the AD docket. rmajette on PROD1PC64 with PROPOSALS Relevant Service Information Airbus has issued the following service information. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. • Airbus Service Bulletin A300–57– 0247, including Appendix 01, dated November 7, 2006. • Airbus Service Bulletin A300–57– 6104, including Appendix 01, dated November 7, 2006. • Airbus A300 Airplane Flight Manual (AFM), Appendix— Configuration Deviation List, Page 6.03.27, dated February 1, 1993. • Airbus A300–600 AFM, Appendix—Configuration Deviation List, Page 6.03.27, dated May 1, 1992. VerDate Aug<31>2005 15:19 Jul 09, 2007 Jkt 211001 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 167 products of U.S. registry. We also estimate that it would take about 16 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 $213,760, or $1,280 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2007–28665; Directorate Identifier 2007–NM–081–AD. Comments Due Date (a) We must receive comments by August 9, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300 and A300–600 series airplanes, all certified models, all serial numbers, certificated in any category; except Airbus Model A300–600 series airplanes from Manufacturer’s Serial Number 0872 onward, which received E:\FR\FM\10JYP1.SGM 10JYP1 37479 Federal Register / Vol. 72, No. 131 / Tuesday, July 10, 2007 / Proposed Rules application of Airbus modifications 13245 and 13282 during production. Subject (d) Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Three cases of outer deflector panel found detached or broken during ground inspection have been reported by operators to Airbus. The affected deflector panel is the most outboard of the two outer deflectors. In addition, an operator has also reported a missing portion of hinge on one panel. The missing portion of hinge is held to the structure through one Camloc fastener. Mishandling or failure of the small portion of hinge located inboard of the affected deflector panel is suspected to be the main cause of the deflector damage. This can cause misalignment of the deflector panel followed by hinge pin migration and possible further damages to the deflector on flap retraction. If not corrected, such situation could lead to the loss of deflector panel and injured people on the ground. The aim of this Airworthiness Directive (AD) is to mandate the one time inspection to detect and prevent damage to inner and outer shroud box deflectors. The corrective action includes repairing any discrepancy, or removing the affected deflector door according to the Configuration Deviation List (CDL). Actions and Compliance (f) Within 18 months after the effective date of this AD, unless already done, do a detailed visual inspection of the inner and outer shroud box flap deflectors in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0247, including Appendix 01, dated November 7, 2006; or Airbus Service Bulletin A300–57–6104, including Appendix 01, dated November 7, 2006; as applicable. (1) If any discrepancy or damage is found, before next flight do the action in paragraph (f)(1)(i) or (f)(1)(ii) of this AD. (i) Repair the affected flap deflector in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0247, including Appendix 01, dated November 7, 2006; or Airbus Service Bulletin A300–57–6104, including Appendix 01, dated November 7, 2006; as applicable. (ii) Remove the affected deflector door as described in Airbus A300 Airplane Flight Manual (AFM), Appendix—Configuration Deviation List, Page 6.03.27, dated February 1, 1993; or Airbus A300–600 AFM, Appendix—Configuration Deviation List, Page 6.03.27, dated May 1, 1992; as applicable. The removed door may be reinstalled once it has been repaired in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0247, including Appendix 01, dated November 7, 2006; or Airbus Service Bulletin A300–57–6104, including Appendix 01, dated November 7, 2006; as applicable. (2) Report to Airbus the results of the inspection done in accordance with paragraph (f) of this AD, using the inspection report included in Appendix 01 of the applicable service bulletin specified in paragraph (f) of this AD. 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, ANM–116, Transport Airplane Directorate, International Branch, 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, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2007–0062, dated March 7, 2007, and the service information identified in Table 1 of this AD, for related information. TABLE 1.—AIRBUS SERVICE INFORMATION Service information Airbus Airbus Airbus Airbus Date Service Bulletin A300–57–0247, including Appendix 01 ................................................................................................. Service Bulletin A300–57–6104, including Appendix 01 ................................................................................................. A300 Airplane Flight Manual, Appendix—Configuration Deviation List, Page 6.03.27 .................................................. A300–600 Airplane Flight Manual, Appendix—Configuration Deviation List, Page 6.03.27 .......................................... Issued in Renton, Washington, on June 26, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–13354 Filed 7–9–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28661; Directorate Identifier 2007–NM–013AD] rmajette on PROD1PC64 with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–600, –700, –700C, –800, and –900 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: VerDate Aug<31>2005 15:19 Jul 09, 2007 Jkt 211001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 November 7, 2006. November 7, 2006. February 1, 1993. May 1, 1992. SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 737–600, –700, –700C, –800, and –900 series airplanes. This proposed AD would require installation of an automatic shutoff system for the center tank fuel boost pumps, installation of a placard in the airplane flight deck if necessary, and concurrent modification of the P5–2 fuel control module assembly. This proposed AD would also require revisions to the Limitations and Normal Procedures sections of the airplane flight manual to advise the flightcrew of certain operating restrictions for airplanes equipped with an automated center tank fuel pump shutoff control. This proposed AD would also require a E:\FR\FM\10JYP1.SGM 10JYP1

Agencies

[Federal Register Volume 72, Number 131 (Tuesday, July 10, 2007)]
[Proposed Rules]
[Pages 37477-37479]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13354]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28665; Directorate Identifier 2007-NM-081-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    Three cases of outer deflector panel found detached or broken 
during ground inspection have been reported to Airbus. * * * [A]n 
operator has also reported a missing portion of hinge on one panel. 
* * * Mishandling or failure of the small portion of hinge located 
inboard of the affected deflector panel is suspected to be the main 
cause of the deflector damage. This can cause misalignment of the 
deflector panel followed by hinge pin migration and possible further 
damages to the deflector on flap retraction. If not corrected, such 
situation could lead to the loss of deflector panel and injured 
people on the ground.

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 August 9, 2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: https://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD

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

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28665; Directorate Identifier 2007-NM-081-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

[[Page 37478]]

closing date and may amend this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2007-0062, dated March 7, 2007 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Three cases of outer deflector panel found detached or broken 
during ground inspection have been reported by operators to Airbus. 
The affected deflector panel is the most outboard of the two outer 
deflectors. In addition, an operator has also reported a missing 
portion of hinge on one panel. The missing portion of hinge is held 
to the structure through one Camloc fastener.
    Mishandling or failure of the small portion of hinge located 
inboard of the affected deflector panel is suspected to be the main 
cause of the deflector damage.
    This can cause misalignment of the deflector panel followed by 
hinge pin migration and possible further damages to the deflector on 
flap retraction. If not corrected, such situation could lead to the 
loss of deflector panel and injured people on the ground.
    The aim of this Airworthiness Directive (AD) is to mandate the 
one time inspection to detect and prevent damage to inner and outer 
shroud box deflectors.

The corrective action includes repairing any discrepancy, or removing 
the affected deflector door according to the Configuration Deviation 
List (CDL). You may obtain further information by examining the MCAI in 
the AD docket.

Relevant Service Information

    Airbus has issued the following service information. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.
     Airbus Service Bulletin A300-57-0247, including Appendix 
01, dated November 7, 2006.
     Airbus Service Bulletin A300-57-6104, including Appendix 
01, dated November 7, 2006.
     Airbus A300 Airplane Flight Manual (AFM), Appendix--
Configuration Deviation List, Page 6.03.27, dated February 1, 1993.
     Airbus A300-600 AFM, Appendix--Configuration Deviation 
List, Page 6.03.27, dated May 1, 1992.

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 167 products of U.S. registry. We also estimate that 
it would take about 16 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 $213,760, or $1,280 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-2007-28665; Directorate Identifier 2007-NM-
081-AD.

Comments Due Date

    (a) We must receive comments by August 9, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 and A300-600 series 
airplanes, all certified models, all serial numbers, certificated in 
any category; except Airbus Model A300-600 series airplanes from 
Manufacturer's Serial Number 0872 onward, which received

[[Page 37479]]

application of Airbus modifications 13245 and 13282 during 
production.

Subject

    (d) Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Three cases of outer deflector panel found detached or broken 
during ground inspection have been reported by operators to Airbus. 
The affected deflector panel is the most outboard of the two outer 
deflectors. In addition, an operator has also reported a missing 
portion of hinge on one panel. The missing portion of hinge is held 
to the structure through one Camloc fastener.
    Mishandling or failure of the small portion of hinge located 
inboard of the affected deflector panel is suspected to be the main 
cause of the deflector damage.
    This can cause misalignment of the deflector panel followed by 
hinge pin migration and possible further damages to the deflector on 
flap retraction.
    If not corrected, such situation could lead to the loss of 
deflector panel and injured people on the ground.
    The aim of this Airworthiness Directive (AD) is to mandate the 
one time inspection to detect and prevent damage to inner and outer 
shroud box deflectors.

The corrective action includes repairing any discrepancy, or 
removing the affected deflector door according to the Configuration 
Deviation List (CDL).

Actions and Compliance

    (f) Within 18 months after the effective date of this AD, unless 
already done, do a detailed visual inspection of the inner and outer 
shroud box flap deflectors in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0247, including 
Appendix 01, dated November 7, 2006; or Airbus Service Bulletin 
A300-57-6104, including Appendix 01, dated November 7, 2006; as 
applicable.
    (1) If any discrepancy or damage is found, before next flight do 
the action in paragraph (f)(1)(i) or (f)(1)(ii) of this AD.
    (i) Repair the affected flap deflector in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-0247, 
including Appendix 01, dated November 7, 2006; or Airbus Service 
Bulletin A300-57-6104, including Appendix 01, dated November 7, 
2006; as applicable.
    (ii) Remove the affected deflector door as described in Airbus 
A300 Airplane Flight Manual (AFM), Appendix--Configuration Deviation 
List, Page 6.03.27, dated February 1, 1993; or Airbus A300-600 AFM, 
Appendix--Configuration Deviation List, Page 6.03.27, dated May 1, 
1992; as applicable. The removed door may be reinstalled once it has 
been repaired in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-0247, including Appendix 01, dated 
November 7, 2006; or Airbus Service Bulletin A300-57-6104, including 
Appendix 01, dated November 7, 2006; as applicable.
    (2) Report to Airbus the results of the inspection done in 
accordance with paragraph (f) of this AD, using the inspection 
report included in Appendix 01 of the applicable service bulletin 
specified in paragraph (f) of this AD.

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, ANM-
116, Transport Airplane Directorate, International Branch, 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, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2007-0062, dated March 7, 2007, and the 
service information identified in Table 1 of this AD, for related 
information.

                  Table 1.--Airbus Service Information
------------------------------------------------------------------------
         Service information                          Date
------------------------------------------------------------------------
Airbus Service Bulletin A300-57-0247,  November 7, 2006.
 including Appendix 01.
Airbus Service Bulletin A300-57-6104,  November 7, 2006.
 including Appendix 01.
Airbus A300 Airplane Flight Manual,    February 1, 1993.
 Appendix--Configuration Deviation
 List, Page 6.03.27.
Airbus A300-600 Airplane Flight        May 1, 1992.
 Manual, Appendix--Configuration
 Deviation List, Page 6.03.27.
------------------------------------------------------------------------


    Issued in Renton, Washington, on June 26, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-13354 Filed 7-9-07; 8:45 am]
BILLING CODE 4910-13-P

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