Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-200 and -300 Series Airplanes, 62566-62568 [E7-21686]

Download as PDF 62566 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations mstockstill on PROD1PC66 with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA published Special Federal Aviation Regulation 88 (SFAR 88) in June 2001. SFAR 88 required a safety review of the aircraft Fuel Tank System to determine that the design meets the requirements of FAR (Federal Aviation Regulation) § 25.901 and § 25.981(a) and (b). A similar regulation has been recommended by the JAA (Joint Aviation Authorities) to the European National Aviation Authorities in JAA letter 04/00/02/ 07/03–L024 of 3 February 2003. The review was requested to be mandated by NAA’s (National Aviation Authorities) using JAR (Joint Aviation Regulation) § 25.901(c), § 25.1309. In August 2005 EASA (European Aviation Safety Agency) published a policy statement on the process for developing instructions for maintenance and inspection of Fuel Tank System ignition source prevention (EASA D 2005/CPRO, www.easa.eu.int/home/ cert_policy_statements_en.html) that also included the EASA expectations with regard to compliance times of the corrective actions on the ‘unsafe and the not unsafe part of the harmonised design review results. On a global scale the TC (type certificate) holders committed themselves to the EASA published compliance dates (see EASA policy statement). The EASA policy statement has been revised in March 2006: The date of 31–12–2005 for the unsafe related actions has now been set at 01–07–2006. Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition’ as defined in FAA’s memo 2003–112–15 ‘SFAR 88—Mandatory Action Decision Criteria’. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers’ requirements. This EASA Airworthiness Directive mandates the Fuel System Airworthiness Limitations (comprising maintenance/ inspection tasks and Critical Design Configuration Control Limitations (CDCCL)) for the type of aircraft, that resulted from the design reviews and the JAA recommendation and EASA policy statement mentioned above. The corrective action is revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 3 months after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate the maintenance and inspection instructions in Part 1 of Saab Fuel Airworthiness Limitations 2000 LKS 009032, dated February 14, 2006. For all tasks identified in VerDate Aug<31>2005 17:31 Nov 05, 2007 Jkt 214001 Part 1 of Saab Fuel Airworthiness Limitations 2000 LKS 009032, dated February 14, 2006, the initial compliance times start from the effective date of this AD, and the repetitive inspections must be accomplished thereafter at the interval specified in Part 1 of Saab Fuel Airworthiness Limitations 2000 LKS 009032, dated February 14, 2006. (2) Within 12 months after the effective date of this AD, revise the ALS of the Instructions for Continued Airworthiness to incorporate the CDCCLs as defined in Part 2 of Saab Fuel Airworthiness Limitations 2000 LKS 009032, dated February 14, 2006. (3) Except as provided by paragraph (g) of this AD: After accomplishing the actions specified in paragraphs (f)(1) and (f)(2) of this AD, no alternative inspection, inspection intervals, or CDCCLs may be used. (4) Where Saab Fuel Airworthiness Limitations 2000 LKS 009032, dated February 14, 2006, allows for exceptional short-term extensions, an exception is acceptable to the FAA if it is approved by the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. FAA AD Differences Note 2: 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: Mike Borfitz, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2677; 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 2006–0199, dated July 11, 2006, and Saab Fuel Airworthiness Limitations 2000 LKS 009032, dated February 14, 2006, for related information. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Material Incorporated by Reference (i) You must use Saab Fuel Airworthiness Limitations 2000 LKS 009032, dated February 14, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (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 Saab Aircraft AB, SAAB Aircraft Product Support, S–581.88, ¨ Linkoping, Sweden. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or 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/cfr/ibrlocations.html. Issued in Renton, Washington, on October 27, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–21674 Filed 11–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28925; Directorate Identifier 2007–NM–123–AD; Amendment 39–15248; AD 2007–23–02] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200 and –300 Series Airplanes, and Model A340–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 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: During ground inspection of an A340–311 aircraft, it has been discovered that 5 fasteners were missing between Frame (FR) 18 and FR19 on longitudinal joint at stringer 28RH (right hand). Further investigations have revealed that the missing fasteners have not been installed in production due to incorrect production instructions. E:\FR\FM\06NOR1.SGM 06NOR1 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations If not corrected, this situation could affect the structural integrity of the aircraft in the area of stringer 28 between FR18 and FR19 at longitudinal joint. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 11, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 11, 2007. 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: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; 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 16, 2007 (72 FR 45970). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: mstockstill on PROD1PC66 with RULES During ground inspection of an A340–311 aircraft, it has been discovered that 5 fasteners were missing between Frame (FR) 18 and FR19 on longitudinal joint at stringer 28RH (right hand). Further investigations have revealed that the missing fasteners have not been installed in production due to incorrect production instructions. If not corrected, this situation could affect the structural integrity of the aircraft in the area of stringer 28 between FR18 and FR19 at longitudinal joint. In order to re-establish the structural strength of the aircraft, this Airworthiness Directive (AD) renders mandatory the inspection of the longitudinal joint at stringer 28 RH between FR18 and FR19 [for missing fasteners]. For airplanes on which any fastener is missing, the corrective actions include doing a detailed visual inspection for cracking of the adjacent fastener area from the outside, without removing the fasteners; and if no crack is found, doing a rotating probe inspection for cracks of the adjacent fastener holes after removing the fasteners, and replacing VerDate Aug<31>2005 16:30 Nov 05, 2007 Jkt 214001 any missing fastener. The corrective actions also include contacting Airbus for repair instructions and repair if fasteners are not at nominal diameter or if any crack is found. 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 received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 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 9 products of U.S. registry. We also estimate that it will take about 4 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $2,880, or $320 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 62567 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I E:\FR\FM\06NOR1.SGM 06NOR1 62568 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations 2007–23–02 Airbus: Amendment 39–15248. Docket No. FAA–2007–28925; Directorate Identifier 2007–NM–123–AD. FAA AD Differences Effective Date Note: This AD differs from the MCAI and/ or service information as follows: No differences. (a) This airworthiness directive (AD) becomes effective December 11, 2007. Other FAA AD Provisions Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330– 200 and –300 series airplanes and Model A340–200 and –300 series airplanes; certificated in any category; all manufacturer’s serial numbers (MSN) up to MSN 0402 included, except MSN 051. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: During ground inspection of an A340–311 aircraft, it has been discovered that 5 fasteners were missing between Frame (FR) 18 and FR19 on longitudinal joint at stringer 28RH (right hand). Further investigations have revealed that the missing fasteners have not been installed in production due to incorrect production instructions. If not corrected, this situation could affect the structural integrity of the aircraft in the area of stringer 28 between FR18 and FR19 at longitudinal joint. In order to re-establish the structural strength of the aircraft, this Airworthiness Directive (AD) renders mandatory the inspection of the longitudinal joint at stringer 28 RH between FR18 and FR19 [for missing fasteners]. For airplanes on which any fastener is missing, the corrective actions include doing a detailed visual inspection for cracking of the adjacent fastener area from the outside, without removing the fasteners; and if no crack is found, doing a rotating probe inspection for cracks of the adjacent fastener holes after removing the fasteners, and replacing any missing fastener. The corrective actions also include contacting Airbus for repair instructions and repair if fasteners are not at nominal diameter or if any crack is found. mstockstill on PROD1PC66 with RULES Actions and Compliance (f) Before the accumulation of 14,000 flight cycles from the first flight of the aircraft, or within 1,500 flight cycles following the effective date of this AD, whichever occurs later, unless already done, do the following actions: Perform a detailed visual inspection of the longitudinal joint at stringer 28 RH between FR18 and FR19 for missing fasteners, and do all applicable corrective actions before further flight, in accordance with the instructions defined in Airbus Service Bulletin A330–53–3170 or A340–53– 4175, both dated March 27, 2007. VerDate Aug<31>2005 16:30 Nov 05, 2007 Jkt 214001 (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; 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 2007– 0125, dated May 4, 2007, and Airbus Service Bulletins A330–53–3170 and A340–53–4175, both dated March 27, 2007, for related information. Material Incorporated by Reference (i) You must use the service information specified in Table 1 of this AD to do the actions required by this AD, unless the AD specifies otherwise. (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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin A330–53–3170, excluding Appendix 01 ........ A340–53–4175, excluding Appendix 01 ........ Date March 27, 2007. March 27, 2007. Issued in Renton, Washington, on October 27, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–21686 Filed 11–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28882; Directorate Identifier 2007–NM–035–AD; Amendment 39–15247; AD 2007–23–01] RIN 2120–AA64 Airworthiness Directives; Goodrich Evacuation Systems Approved Under Technical Standard Order (TSO) TSO– C69b and Installed on Airbus Model A330–200 and –300 Series Airplanes, Model A340–200 and –300 Series Airplanes, and Model A340–541 and –642 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to Goodrich evacuation systems approved under TSO–C69b and installed on certain Airbus Model A330–200 and –300 series airplanes, Model A340–200 and –300 series airplanes, and Model A340–541 and –642 airplanes. That AD currently requires inspecting to determine the part number of the pressure relief valves on the affected Goodrich evacuation systems, and corrective action if necessary. For certain airplanes, this new AD requires an additional inspection to determine the part number of the pressure relief valves, and corrective action if necessary. This AD results from a report indicating that, during maintenance testing, the pressure relief valves on the affected Goodrich evacuation systems did not seal when activated, which caused the pressure in the escape slide/raft to drop below the minimum allowable raft mode pressure. We are issuing this AD E:\FR\FM\06NOR1.SGM 06NOR1

Agencies

[Federal Register Volume 72, Number 214 (Tuesday, November 6, 2007)]
[Rules and Regulations]
[Pages 62566-62568]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-21686]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28925; Directorate Identifier 2007-NM-123-AD; 
Amendment 39-15248; AD 2007-23-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200 and -300 Series 
Airplanes, and Model A340-200 and -300 Series 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:

    During ground inspection of an A340-311 aircraft, it has been 
discovered that 5 fasteners were missing between Frame (FR) 18 and 
FR19 on longitudinal joint at stringer 28RH (right hand).

    Further investigations have revealed that the missing fasteners 
have not been installed in production due to incorrect production 
instructions.


[[Page 62567]]


    If not corrected, this situation could affect the structural 
integrity of the aircraft in the area of stringer 28 between FR18 
and FR19 at longitudinal joint.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective December 11, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 11, 
2007.

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: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; 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 16, 2007 (72 
FR 45970). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During ground inspection of an A340-311 aircraft, it has been 
discovered that 5 fasteners were missing between Frame (FR) 18 and 
FR19 on longitudinal joint at stringer 28RH (right hand).

    Further investigations have revealed that the missing fasteners 
have not been installed in production due to incorrect production 
instructions.

    If not corrected, this situation could affect the structural 
integrity of the aircraft in the area of stringer 28 between FR18 
and FR19 at longitudinal joint.

    In order to re-establish the structural strength of the 
aircraft, this Airworthiness Directive (AD) renders mandatory the 
inspection of the longitudinal joint at stringer 28 RH between FR18 
and FR19 [for missing fasteners].

For airplanes on which any fastener is missing, the corrective actions 
include doing a detailed visual inspection for cracking of the adjacent 
fastener area from the outside, without removing the fasteners; and if 
no crack is found, doing a rotating probe inspection for cracks of the 
adjacent fastener holes after removing the fasteners, and replacing any 
missing fastener. The corrective actions also include contacting Airbus 
for repair instructions and repair if fasteners are not at nominal 
diameter or if any crack is found. 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 received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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 9 products of U.S. 
registry. We also estimate that it will take about 4 work-hours per 
product to comply with the basic requirements of this AD. The average 
labor rate is $80 per work-hour. Based on these figures, we estimate 
the cost of this AD to the U.S. operators to be $2,880, or $320 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

0
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:


[[Page 62568]]


2007-23-02 Airbus: Amendment 39-15248. Docket No. FAA-2007-28925; 
Directorate Identifier 2007-NM-123-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
11, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-200 and -300 series 
airplanes and Model A340-200 and -300 series airplanes; certificated 
in any category; all manufacturer's serial numbers (MSN) up to MSN 
0402 included, except MSN 051.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    During ground inspection of an A340-311 aircraft, it has been 
discovered that 5 fasteners were missing between Frame (FR) 18 and 
FR19 on longitudinal joint at stringer 28RH (right hand).

    Further investigations have revealed that the missing fasteners 
have not been installed in production due to incorrect production 
instructions.

    If not corrected, this situation could affect the structural 
integrity of the aircraft in the area of stringer 28 between FR18 
and FR19 at longitudinal joint.

    In order to re-establish the structural strength of the 
aircraft, this Airworthiness Directive (AD) renders mandatory the 
inspection of the longitudinal joint at stringer 28 RH between FR18 
and FR19 [for missing fasteners].

For airplanes on which any fastener is missing, the corrective 
actions include doing a detailed visual inspection for cracking of 
the adjacent fastener area from the outside, without removing the 
fasteners; and if no crack is found, doing a rotating probe 
inspection for cracks of the adjacent fastener holes after removing 
the fasteners, and replacing any missing fastener. The corrective 
actions also include contacting Airbus for repair instructions and 
repair if fasteners are not at nominal diameter or if any crack is 
found.

Actions and Compliance

    (f) Before the accumulation of 14,000 flight cycles from the 
first flight of the aircraft, or within 1,500 flight cycles 
following the effective date of this AD, whichever occurs later, 
unless already done, do the following actions: Perform a detailed 
visual inspection of the longitudinal joint at stringer 28 RH 
between FR18 and FR19 for missing fasteners, and do all applicable 
corrective actions before further flight, in accordance with the 
instructions defined in Airbus Service Bulletin A330-53-3170 or 
A340-53-4175, both dated March 27, 2007.

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, 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: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2797; 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 2007-0125, dated May 4, 2007, and Airbus Service Bulletins 
A330-53-3170 and A340-53-4175, both dated March 27, 2007, for 
related information.

Material Incorporated by Reference

    (i) You must use the service information specified in Table 1 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.
    (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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    (3) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-
locations.html.

              Table 1.--Material Incorporated by Reference
------------------------------------------------------------------------
               Airbus Service Bulletin                       Date
------------------------------------------------------------------------
A330-53-3170, excluding Appendix 01.................     March 27, 2007.
A340-53-4175, excluding Appendix 01.................     March 27, 2007.
------------------------------------------------------------------------


    Issued in Renton, Washington, on October 27, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-21686 Filed 11-5-07; 8:45 am]
BILLING CODE 4910-13-P