Airworthiness Directives; Airbus Model A330 Airplanes, 12555-12557 [E7-4740]

Download as PDF Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations 12555 TABLE 5.—SERVICE BULLETINS ACCOMPLISHED PREVIOUSLY—Continued Airbus service bulletin Revision level Date A310–78–2023 ........................................................................ A310–78–2024 ........................................................................ A310–78–2025 ........................................................................ Original ................................................................................... Original ................................................................................... Original ................................................................................... October 7, 2003. October 15, 2003. July 23, 2004. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (j) French airworthiness directive F– 2004–165, dated October 13, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use the applicable Airbus service bulletins specified in Table 6 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. 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: http://www.archives.gov/ federal-register/cfr/ibr-locations.html. TABLE 6.—MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin Revision level A300–78–6021, including Appendices 01 and 02 .................. A300–78–6022, including Appendices 01 and 02 .................. A300–78–6024 ........................................................................ A300–78–6025 ........................................................................ A310–78–2022, including Appendices 01 and 02 .................. A310–78–2023 ........................................................................ A310–78–2024, including Appendices 01 and 02 .................. A310–78–2025 ........................................................................ Issued in Renton, Washington, on March 5, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–4734 Filed 3–15–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26324; Directorate Identifier 2006–NM–214–AD; Amendment 39–14993; AD 2007–06–12] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A330–300 airplanes. That AD currently requires reinforcement of the structure VerDate Aug<31>2005 15:23 Mar 15, 2007 Jkt 211001 02 02 01 01 02 01 01 01 ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ of the center fuselage by installing external stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and related investigative and corrective actions. This new AD requires additional reinforcement of the structure of the center fuselage by installing external stiffeners (butt straps) at frame FR53.3 on the fuselage skin between LH and RH STR13, and related investigative and other specified actions. This AD also adds airplanes to the applicability. This AD results from cracking found at the circumferential joint of FR53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage. This AD becomes effective April 20, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 20, 2007. On October 19, 2005 (70 FR 57732, October 4, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus DATES: PO 00000 Frm 00011 Date Fmt 4700 Sfmt 4700 June 8, 2005. June 8, 2005. April 22, 2005. April 22, 2005. July 18, 2006. April 22, 2005. June 13, 2005. April 22, 2005. Service Bulletin A330–53–3127, Revision 01, dated November 21, 2003. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. 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: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on E:\FR\FM\16MRR1.SGM 16MRR1 12556 Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2005–20–07, amendment 39–14300 (70 FR 57732, October 4, 2005). The existing AD applies to certain Airbus Model A330–300 series airplanes. That NPRM was published in the Federal Register on November 15, 2006 (71 FR 66472). That NPRM proposed to continue to require reinforcement of the structure of the center fuselage by installing external stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and related investigative and corrective actions. That NPRM also proposed to require additional reinforcement of the structure of the center fuselage by installing external stiffeners (butt straps) at frame FR53.3 on the fuselage skin between LH and RH STR13, and related investigative and other specified actions. That NPRM also proposed to add airplanes to the applicability. sroberts on PROD1PC70 with RULES Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Revise Paragraph (h) Airbus requests that we revise the phrase ‘‘For all airplanes * * *’’ in paragraph (h) of the NPRM to duplicate paragraph 2 of European Aviation Safety Agency (EASA) airworthiness directive 2006–0266, dated August 30, 2006, as follows: ‘‘For all A330–200 and –300 series aircraft [as listed in the applicability of this directive] which have received embodiment of AIRBUS modification 41652S11819.’’ We agree to clarify paragraph (h) of this AD. The term ‘‘for all airplanes’’ in paragraph (h) of the NPRM applies to the airplanes identified in paragraph (c) of the NPRM (the applicability of the NPRM). Even though paragraph (h) of the NPRM is essentially the same as paragraph 2 of EASA airworthiness directive 2006–0266, we have revised paragraph (h) of this AD as follows: ‘‘For Airbus Model A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes, on which Airbus Modification 41652S11819 has been incorporated in production or in accordance with paragraph (f) of this AD, except those VerDate Aug<31>2005 15:23 Mar 15, 2007 Jkt 211001 airplanes on which Airbus Modification 49202 has been incorporated in production * * *.’’ This change has not expanded the scope of this AD. Request To Include Note Airbus requests that we revise the NPRM to include Note 2 of EASA airworthiness directive 2006–0266: ‘‘Notwithstanding the compliance times referenced above, EASA supports the Airbus recommendation to embody SB A330–53–3143 at latest within 8,300 FC or 29,200 FH, whichever occurs first, in order to reduce the extent of any required repairs.’’ We disagree with including the note. We acknowledge that accomplishing the required actions sooner could reduce the extent of repairs needed in the future. However, it is not appropriate and, therefore, not the FAA’s practice to state recommendations in an AD. We have not revised this AD in this regard. Request To Revise Discussion Section Airbus requests that we revise the Discussion section of the NPRM to state the unsafe condition was found during fatigue tests (EF2) of the fuselage. We agree with Airbus’s statement. However, that portion of the Discussion section is not retained in this final rule. We have not revised this AD in this regard. Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance Currently, the action required by AD 2005–20–07 and retained in this AD affects 12 airplanes of U.S. registry. However, we have been advised that all affected U.S. operators have already accomplished that action. If an affected airplane is imported and placed on the U.S. Register in the future, the action required by AD 2005–20–07 takes about 315 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost about $8,920 per airplane. Based on these figures, the estimated cost of the currently required action is $34,120 per airplane. The new action affects about 27 airplanes of U.S. registry. The new action takes about 316 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 about $9,160 per airplane. Based on these figures, the estimated cost of the new action specified in this AD for U.S. operators is $929,880, or $34,440 per airplane. 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 have 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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. 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, 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 E:\FR\FM\16MRR1.SGM 16MRR1 Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations ´ ´ Contact the FAA/Direction Generale de l’Aviation Civile (DGAC)/European Aviation Safety Agency (EASA) for Certain Repair Instructions 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 Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14300 (70 FR 57732, October 4, 2005) and by adding the following new airworthiness directive (AD): I 2007–06–12 Airbus: Amendment 39–14993. Docket No. FAA–2006–26324; Directorate Identifier 2006–NM–214–AD. (a) This AD becomes effective April 20, 2007. Affected ADs (b) This AD supersedes AD 2005–20–07. Applicability (c) This AD applies to Airbus Model A330– 201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes, certificated in any category; except those on which Airbus Modification 49202 has been incorporated in production. Unsafe Condition (d) This AD results from cracking found at the circumferential joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage. 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. Requirements of AD 2005–20–07 Installation for Model A330–300 Series Airplanes sroberts on PROD1PC70 with RULES Related Information (k) EASA airworthiness directive 2006– 0266, dated August 30, 2006, also addresses the subject of this AD. (g) For Airbus Model A330–301, –321, –322, –323, –341, –342, and –343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: If any crack is detected during the related investigative actions (rototest) required by paragraph (f) of this AD, before further flight, repair the crack according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the DGAC (or its delegated agent); or the EASA (or its delegated agent). Material Incorporated by Reference (l) You must use Airbus Service Bulletin A330–53–3127, Revision 01, dated November 21, 2003; and Airbus Service Bulletin A330– 53–3143, Revision 01, including Appendix 01, dated June 29, 2006; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A330–53–3143, Revision 01, including Appendix 01, dated June 29, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On October 19, 2005 (70 FR 57732, October 4, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A330– 53–3127, Revision 01, dated November 21, 2003. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. 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 the NARA, call (202) 741–6030, or go to: http://www.archives.gov/federalregister/cfr/ibr-locations.html. New Requirements of This AD Installation for Model A330–200 and –300 Series Airplanes Effective Date (f) For Airbus Model A330–301, –321, –322, –323, –341, –342, and –343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: At the later of the times in paragraphs (f)(1) and (f)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and do all related investigative and corrective actions before further flight. Except as provided by paragraph (g) of this AD, do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3127, Revision 01, dated November 21, 2003. (1) Before the accumulation of 14,700 total flight cycles or 51,400 total flight hours, whichever occurs earlier. (2) Within 6 months after October 19, 2005 (the effective date of AD 2005–20–07). VerDate Aug<31>2005 15:23 Mar 15, 2007 Jkt 211001 12557 (h) For Airbus Model A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes, on which Airbus Modification 41652S11819 has been incorporated in production or in accordance with paragraph (f) of this AD, except those airplanes on which Airbus Modification 49202 has been incorporated in production: At the later of the times in paragraphs (h)(1) and (h)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between LH and RH STR13; and do all related investigative and other specified actions before further flight, as applicable. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3143, Revision 01, including Appendix 01, dated June 29, 2006; except if any crack is detected during a related investigative action (rototest), before further flight, repair the crack using a method approved by the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). (1) Before the accumulation of 17,600 total flight cycles or 61,600 total flight hours, whichever occurs earlier. (2) Within 6 months after the effective date of this AD. Credit for Actions Done in Accordance With Previous Service Bulletin (i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A330–53–3143, including Appendix 01, dated December 24, 2004, are acceptable for compliance with the corresponding requirements of paragraph (h) of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on March 7, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–4740 Filed 3–15–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26401; Directorate Identifier 2006–CE–72–AD; Amendment 39– 14987; AD 2007–06–06] RIN 2120–AA64 Airworthiness Directives; B–N Group Ltd. BN–2, BN–2A, BN–2B, BN–2T, and BN–2T–4R Series (All Individual Models Included in Type Certificate Data Sheet (TCDS) A17EU, Revision 16, Dated December 9, 2002), and BN– 2A–Mklll Trislander Series (All Individual Models Included in Type Certificate Data Sheet (TCDS) A29EU, Revision 4, Dated December 9, 2002) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: E:\FR\FM\16MRR1.SGM 16MRR1

Agencies

[Federal Register Volume 72, Number 51 (Friday, March 16, 2007)]
[Rules and Regulations]
[Pages 12555-12557]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4740]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26324; Directorate Identifier 2006-NM-214-AD; 
Amendment 39-14993; AD 2007-06-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A330-300 airplanes. That AD 
currently requires reinforcement of the structure of the center 
fuselage by installing external stiffeners (butt straps) at frame (FR) 
53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) 
stringer (STR) 13, and related investigative and corrective actions. 
This new AD requires additional reinforcement of the structure of the 
center fuselage by installing external stiffeners (butt straps) at 
frame FR53.3 on the fuselage skin between LH and RH STR13, and related 
investigative and other specified actions. This AD also adds airplanes 
to the applicability. This AD results from cracking found at the 
circumferential joint of FR53.3. We are issuing this AD to prevent 
fatigue cracking of the fuselage, which could result in reduced 
structural integrity of the fuselage.

DATES: This AD becomes effective April 20, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 20, 
2007.
    On October 19, 2005 (70 FR 57732, October 4, 2005), the Director of 
the Federal Register approved the incorporation by reference of Airbus 
Service Bulletin A330-53-3127, Revision 01, dated November 21, 2003.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

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:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on

[[Page 12556]]

the plaza level of the Nassif Building at the street address stated in 
the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2005-20-07, amendment 
39-14300 (70 FR 57732, October 4, 2005). The existing AD applies to 
certain Airbus Model A330-300 series airplanes. That NPRM was published 
in the Federal Register on November 15, 2006 (71 FR 66472). That NPRM 
proposed to continue to require reinforcement of the structure of the 
center fuselage by installing external stiffeners (butt straps) at 
frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-
hand (RH) stringer (STR) 13, and related investigative and corrective 
actions. That NPRM also proposed to require additional reinforcement of 
the structure of the center fuselage by installing external stiffeners 
(butt straps) at frame FR53.3 on the fuselage skin between LH and RH 
STR13, and related investigative and other specified actions. That NPRM 
also proposed to add airplanes to the applicability.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Revise Paragraph (h)

    Airbus requests that we revise the phrase ``For all airplanes * * 
*'' in paragraph (h) of the NPRM to duplicate paragraph 2 of European 
Aviation Safety Agency (EASA) airworthiness directive 2006-0266, dated 
August 30, 2006, as follows: ``For all A330-200 and -300 series 
aircraft [as listed in the applicability of this directive] which have 
received embodiment of AIRBUS modification 41652S11819.''
    We agree to clarify paragraph (h) of this AD. The term ``for all 
airplanes'' in paragraph (h) of the NPRM applies to the airplanes 
identified in paragraph (c) of the NPRM (the applicability of the 
NPRM). Even though paragraph (h) of the NPRM is essentially the same as 
paragraph 2 of EASA airworthiness directive 2006-0266, we have revised 
paragraph (h) of this AD as follows: ``For Airbus Model A330-201, -202, 
-203, -223, -243, -301, -321, -322, -323, -341, -342, and -343 
airplanes, on which Airbus Modification 41652S11819 has been 
incorporated in production or in accordance with paragraph (f) of this 
AD, except those airplanes on which Airbus Modification 49202 has been 
incorporated in production * * *.'' This change has not expanded the 
scope of this AD.

Request To Include Note

    Airbus requests that we revise the NPRM to include Note 2 of EASA 
airworthiness directive 2006-0266: ``Notwithstanding the compliance 
times referenced above, EASA supports the Airbus recommendation to 
embody SB A330-53-3143 at latest within 8,300 FC or 29,200 FH, 
whichever occurs first, in order to reduce the extent of any required 
repairs.''
    We disagree with including the note. We acknowledge that 
accomplishing the required actions sooner could reduce the extent of 
repairs needed in the future. However, it is not appropriate and, 
therefore, not the FAA's practice to state recommendations in an AD. We 
have not revised this AD in this regard.

Request To Revise Discussion Section

    Airbus requests that we revise the Discussion section of the NPRM 
to state the unsafe condition was found during fatigue tests (EF2) of 
the fuselage.
    We agree with Airbus's statement. However, that portion of the 
Discussion section is not retained in this final rule. We have not 
revised this AD in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the change described 
previously. We have determined that this change will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    Currently, the action required by AD 2005-20-07 and retained in 
this AD affects 12 airplanes of U.S. registry. However, we have been 
advised that all affected U.S. operators have already accomplished that 
action. If an affected airplane is imported and placed on the U.S. 
Register in the future, the action required by AD 2005-20-07 takes 
about 315 work hours per airplane, at an average labor rate of $80 per 
work hour. Required parts cost about $8,920 per airplane. Based on 
these figures, the estimated cost of the currently required action is 
$34,120 per airplane.
    The new action affects about 27 airplanes of U.S. registry. The new 
action takes about 316 work hours per airplane, at an average labor 
rate of $80 per work hour. Required parts cost about $9,160 per 
airplane. Based on these figures, the estimated cost of the new action 
specified in this AD for U.S. operators is $929,880, or $34,440 per 
airplane.

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 have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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. 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, 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:

[[Page 12557]]

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14300 (70 FR 57732, October 4, 2005) and by 
adding the following new airworthiness directive (AD):

2007-06-12 Airbus: Amendment 39-14993. Docket No. FAA-2006-26324; 
Directorate Identifier 2006-NM-214-AD.

Effective Date

    (a) This AD becomes effective April 20, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-20-07.

Applicability

    (c) This AD applies to Airbus Model A330-201, -202, -203, -223, 
-243, -301, -321, -322, -323, -341, -342, and -343 airplanes, 
certificated in any category; except those on which Airbus 
Modification 49202 has been incorporated in production.

Unsafe Condition

    (d) This AD results from cracking found at the circumferential 
joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue 
cracking of the fuselage, which could result in reduced structural 
integrity of the fuselage.

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.

Requirements of AD 2005-20-07

Installation for Model A330-300 Series Airplanes

    (f) For Airbus Model A330-301, -321, -322, -323, -341, -342, and 
-343 airplanes, except those on which Airbus Modification 
41652S11819 has been incorporated in production: At the later of the 
times in paragraphs (f)(1) and (f)(2) of this AD, install the butt 
straps at FR53.3 on the fuselage skin between left-hand (LH) and 
right-hand (RH) stringer (STR) 13, and do all related investigative 
and corrective actions before further flight. Except as provided by 
paragraph (g) of this AD, do all actions in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3127, 
Revision 01, dated November 21, 2003.
    (1) Before the accumulation of 14,700 total flight cycles or 
51,400 total flight hours, whichever occurs earlier.
    (2) Within 6 months after October 19, 2005 (the effective date 
of AD 2005-20-07).

Contact the FAA/Direction G[eacute]n[eacute]rale de l'Aviation Civile 
(DGAC)/European Aviation Safety Agency (EASA) for Certain Repair 
Instructions

    (g) For Airbus Model A330-301, -321, -322, -323, -341, -342, and 
-343 airplanes, except those on which Airbus Modification 
41652S11819 has been incorporated in production: If any crack is 
detected during the related investigative actions (rototest) 
required by paragraph (f) of this AD, before further flight, repair 
the crack according to a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
the DGAC (or its delegated agent); or the EASA (or its delegated 
agent).

New Requirements of This AD

Installation for Model A330-200 and -300 Series Airplanes

    (h) For Airbus Model A330-201, -202, -203, -223, -243, -301, -
321, -322, -323, -341, -342, and -343 airplanes, on which Airbus 
Modification 41652S11819 has been incorporated in production or in 
accordance with paragraph (f) of this AD, except those airplanes on 
which Airbus Modification 49202 has been incorporated in production: 
At the later of the times in paragraphs (h)(1) and (h)(2) of this 
AD, install the butt straps at FR53.3 on the fuselage skin between 
LH and RH STR13; and do all related investigative and other 
specified actions before further flight, as applicable. Do all 
actions in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-53-3143, Revision 01, including Appendix 01, 
dated June 29, 2006; except if any crack is detected during a 
related investigative action (rototest), before further flight, 
repair the crack using a method approved by the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent).
    (1) Before the accumulation of 17,600 total flight cycles or 
61,600 total flight hours, whichever occurs earlier.
    (2) Within 6 months after the effective date of this AD.

Credit for Actions Done in Accordance With Previous Service Bulletin

    (i) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A330-53-3143, including 
Appendix 01, dated December 24, 2004, are acceptable for compliance 
with the corresponding requirements of paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (k) EASA airworthiness directive 2006-0266, dated August 30, 
2006, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Airbus Service Bulletin A330-53-3127, Revision 
01, dated November 21, 2003; and Airbus Service Bulletin A330-53-
3143, Revision 01, including Appendix 01, dated June 29, 2006; as 
applicable, to perform the actions that are required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Airbus Service Bulletin A330-53-3143, 
Revision 01, including Appendix 01, dated June 29, 2006, in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On October 19, 2005 (70 FR 57732, October 4, 2005), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A330-53-3127, Revision 01, 
dated November 21, 2003.
    (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. 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 the NARA, call (202) 741-6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-4740 Filed 3-15-07; 8:45 am]
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