Airworthiness Directives; Airbus Model A319 and A320 Series Airplanes, 4063-4066 [E8-970]

Download as PDF Federal Register / Vol. 73, No. 16 / Thursday, January 24, 2008 / Rules and Regulations Optional Part Installed DEPARTMENT OF TRANSPORTATION (g) If an affected duct assembly having a part number other than part number 217T2109–12, or a part number other than any part number specified in the applicable figure of Boeing Service Bulletin 767– 21A0167, Revision 1, dated December 19, 2006, is found installed, and that part number is listed as an optional part number in the table in paragraph 3.B.2., ‘‘Optional Part Table,’’ of the Accomplishment Instructions of the service bulletin: No rework is required for that duct assembly only. Parts Installation (h) As of the effective date of this AD, no person may install on any airplane an air distribution system, Gasper air system, forward E/E compartment air supply, or instrument panel cooling supply duct assembly with BMS 8–39 polyurethane foam insulation. 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. Material Incorporated by Reference jlentini on PROD1PC65 with RULES (j) You must use Boeing Service Bulletin 767–21A0167, Revision 1, dated December 19, 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. (3) You may review copies of the service information incorporated by reference 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/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on January 14, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–972 Filed 1–23–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 19:26 Jan 23, 2008 Jkt 214001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29170; Directorate Identifier 2007–NM–075–AD; Amendment 39–15345; AD 2008–02–15] RIN 2120–AA64 Airworthiness Directives; Airbus Model A319 and A320 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: Some taperlocks used in the wing-tofuselage junction at rib 1 were found to be non-compliant with the applicable specification, resulting in a loss of pretension in the fasteners. In such conditions, the structural integrity of the aircraft could be affected. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective February 28, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 28, 2008. 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 Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; 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 September 13, 2007 (72 FR PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 4063 52309). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Some taperlocks used in the wing-tofuselage junction at rib 1 were found to be non-compliant with the applicable specification, resulting in a loss of pretension in the fasteners. In such conditions, the structural integrity of the aircraft could be affected. This Airworthiness Directive mandates a repetitive internal inspection of the lower stiffeners, and a repetitive external inspection of the lower panels in center and outer wing box at level of rib 1 junction. The corrective action includes contacting Airbus for repair instructions and repair 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 considered the comments received. Request To Refer to Revised Service Information The Air Transport Association (ATA), on behalf of one of its members, United Airlines, and Airbus ask that we refer to Airbus Service Bulletins A320–57–1129 and A320–57–1130, both Revision 02, both dated July 17, 2007, for accomplishing the specified actions. We agree with the requests to refer to Revision 02 of Airbus Service Bulletins A320–57–1129 and A320–57–1130. In the NPRM, we referred to Airbus Service Bulletins A320–57–1129, and A320–57–1130, both Revision 01, both dated July 28, 2006, as the appropriate sources of service information for accomplishing the required actions. Revision 02 of the service bulletins updates the operator and aircraft effectivity to show the latest information. No additional work is required by these revisions of the service bulletins. We have changed paragraphs (f)(1) and (f)(2) of this AD to refer to Revision 02 of the service bulletins. We have also changed paragraphs (f)(1) and (f)(2) to give credit to operators that have done the actions previously in accordance with Revision 01 of the service bulletins. We have also revised the sentence giving credit for an earlier service bulletin in paragraph (f)(2) of this AD for clarity. Request To Allow Installation of a Pin and Sleeve Fastener ATA, on behalf of one of its members, Northwest Airlines (NWA), states that installation of a pin-and-sleeve fastener, instead of the taperlok fastener, should be allowed due to the practical difficulties in accomplishing the NPRM E:\FR\FM\24JAR1.SGM 24JAR1 4064 Federal Register / Vol. 73, No. 16 / Thursday, January 24, 2008 / Rules and Regulations policies. Any such differences are highlighted in a NOTE within the AD. as currently written. NWA notes that installation of the taperlok fasteners requires precision drilling and reaming of the tapered hole and countersink, and adds that industry data show that the installation of a MIL–B–85667 pin-andsleeve fastener can be installed by conventional manual drilling and reaming of a standard hole with relative simplicity and still maintain the fatigue strength capability of the taperlok fastener. NWA adds that the fastener capability properties of the MIL–B– 85667 pin-and-sleeve fastener (titanium tapered pin and aluminum sleeve) meet or exceed those of the Airbus taperlok fasteners for tensile, shear, and fatigue strength. NWA provided a table that identifies the fastener properties. We do not agree with the commenters’ request. The commenters have not provided sufficient data to demonstrate that this installation would adequately address the identified unsafe condition. Although the MIL–B–85667 pin-andsleeve fastener material properties may be equal to or better than the taperlok fasteners, there are other considerations in selection of fasteners that must be addressed, in addition to proper drilling and reaming of the tapered hole and countersink. Therefore, we have not changed the AD in this regard. However, any operator may request an alternative method of compliance (AMOC) in accordance with the procedures in paragraph (g) of the AD, provided that sufficient data are submitted to substantiate that the proposed AMOC would provide an acceptable level of safety. 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. Conclusion Regulatory Findings We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the change described previously. This change will neither increase the economic burden on any operator nor increase the scope of the AD. 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. jlentini on PROD1PC65 with RULES 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 VerDate Aug<31>2005 19:26 Jan 23, 2008 Jkt 214001 Costs of Compliance We estimate that this AD will affect 583 products of U.S. registry. We also estimate that it would take about between 16 and 77 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 the AD on U.S. operators to be between $746,240 and $3,591,280, or between $1,280 and $6,160 per product. Authority for This Rulemaking PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 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 2008–02–15 Airbus: Amendment 39–15345. Docket No. FAA–2007–29170; Directorate Identifier 2007–NM–075–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 28, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A319 and A320 series airplanes, certificated in any category, all certified models, all serial numbers (MSN); except airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. Model A320 series airplanes MSN 2164 through MSN 2688 that have partially received Airbus Modification 33421 in production are affected by the requirements of this AD. (1) Model A319 series airplanes that have received Airbus Modifications 28238, 28162, and 28342 in production, or Airbus Modification 33421 in production. (2) Model A320 series airplanes that have received Airbus Modification 33421 fully embodied in production. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: E:\FR\FM\24JAR1.SGM 24JAR1 4065 Federal Register / Vol. 73, No. 16 / Thursday, January 24, 2008 / Rules and Regulations Some taperlocks used in the wing-tofuselage junction at rib 1 were found to be non-compliant with the applicable specification, resulting in a loss of pretension in the fasteners. In such conditions, the structural integrity of the aircraft could be affected. This Airworthiness Directive mandates a repetitive internal inspection of the lower stiffeners, and a repetitive external inspection of the lower panels in center and outer wing box at level of rib 1 junction. The corrective action includes contacting Airbus for repair instructions and repair if any crack is found. Actions and Compliance (f) Unless already done, do the following actions. (1) For A320–200 aircraft: Before the defined threshold or within the defined grace period after the effective date of this AD, whichever occurs later, as listed in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A320–57–1129, Revision 02, dated July 17, 2007, and following the instructions given in the service bulletin, perform an internal ultrasonic inspection of the lower stiffeners in the center and outer wing box at the level of the rib 1 junction to detect cracks, and if any crack is found, before further flight contact Airbus for repair instructions and repair. Repeat this inspection at the intervals defined in paragraph 1.E., ‘‘Compliance,’’ of the service bulletin. Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A320–57–1129, Revision 01, dated July 28, 2006, are acceptable for compliance with the corresponding actions of this paragraph. (2) For all aircraft: Before the defined threshold or within the defined grace period after the effective date of this AD, whichever occurs later, as listed in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A320–57–1130, Revision 02, dated July 17, 2007, and following the instructions given in the service bulletin, perform an external ultrasonic inspection of the lower stiffeners in the center and outer wing box at the level of the rib 1 junction to detect cracks, and if any crack is found, before further flight contact Airbus for repair instructions and repair. Repeat this inspection at the intervals defined in paragraph 1.E., ‘‘Compliance,’’ of the service bulletin. Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A320–57–1130, dated September 10, 2004; or Revision 01, dated July 28, 2006; are acceptable for compliance with the corresponding actions of this paragraph. (3) Modification of the aircraft in accordance with the instructions contained in Airbus Service Bulletins A320–57–1131, A320–57–1137, or A320–57–1140, all dated November 21, 2006; terminates the repetitive inspection requirements of this AD. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: (1) Although the MCAI or service information does not specify a compliance time for corrective action (repair of cracks), paragraphs (f)(1) and (f)(2) of this AD require that the corrective action be done before further flight. (2) Although the MCAI and/or service information specify a compliance time for accomplishing the inspections after the effective date of the MCAI, this AD requires compliance within the specified compliance time after the effective date of this AD. 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 Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; 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 EASA Airworthiness Directive 2007–0067R1, dated June 7, 2007; and Airbus Service Bulletins A320–57–1129 and A320–57–1130, both Revision 02, both dated July 17, 2007; for related information. Material Incorporated by Reference (i) You must use the Airbus 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. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin jlentini on PROD1PC65 with RULES A320–57–1129, A320–57–1130, A320–57–1131, A320–57–1137, A320–57–1140, VerDate Aug<31>2005 including including including including including Appendix Appendix Appendix Appendix Appendix 19:26 Jan 23, 2008 01 01 01 01 01 Revision .............................................................................................. .............................................................................................. and excluding Appendix 02 ................................................. and excluding Appendix 02 ................................................. and excluding Appendix 02 ................................................. Jkt 214001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Date 02 ............................. 02 ............................. Original .................... Original .................... Original .................... July 17, 2007. July 17, 2007. November 21, 2006. November 21, 2006. November 21, 2006. E:\FR\FM\24JAR1.SGM 24JAR1 4066 Federal Register / Vol. 73, No. 16 / Thursday, January 24, 2008 / Rules and Regulations Issued in Renton, Washington, on January 14, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–970 Filed 1–23–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28973; Directorate Identifier 2007–NM–118–AD; Amendment 39–15344; AD 2008–02–14] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–400, –400D, and –400F Series Airplanes; Boeing Model 757 Airplanes; and Boeing Model 767 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing airplanes listed above. This AD requires an inspection of certain lighted pushbutton switches in the flight compartment for configuration ‘D’ master modules and part numbers and corrective action if necessary. This AD also provides an option to inspect panel assemblies for part numbers. This AD results from a report indicating that the integrated drive generator failed in flight due to a possible switch malfunction. We are issuing this AD to ensure that certain lighted pushbutton switches in the flight compartment do not malfunction and cause the flightcrew to be unable to control critical airplane systems and continue safe airplane operation. This AD becomes effective February 28, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of February 28, 2008. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. DATES: jlentini on PROD1PC65 with RULES Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD VerDate Aug<31>2005 19:26 Jan 23, 2008 Jkt 214001 docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 917–6482; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Boeing Model 747–400, –400D, and –400F series airplanes; Boeing Model 757 airplanes; and Boeing Model 767 airplanes. That NPRM was published in the Federal Register on August 16, 2007 (72 FR 45986). That NPRM proposed to require an inspection of certain lighted pushbutton switches in the flight compartment for configuration ‘D’ master modules and part numbers and corrective action if necessary. That NPRM also provided an option to inspect panel assemblies for part numbers. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Support for the NPRM Boeing, the airplane manufacturer, concurs with the content of the NPRM. Request To Remove Reference to Revision 1 of the Service Bulletins Japan Airlines requests that we remove the reference in the NPRM to Boeing Alert Service Bulletins 747– 33A2280 and 767–33A0087, both Revision 1, both dated September 25, 2003 (we referred to those service bulletins as appropriate sources of service information for doing the actions specified in the NPRM). The commenter notes that it has incorporated Boeing Alert Service Bulletins 747–33A2280 and 767–33A0087, both dated December 19, 2001, for its Model 747–400 and Model 767–200/–300 fleets. The commenter notes that it strictly controls the configuration ‘D’ master module. However, the commenter states it did not carry out some top assembly module part number changes according to the PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 instructions of Revision 1 of the service bulletins because in some cases the original top assembly module part number was not indicated anywhere, or was indicated unclearly. The commenter believes that it is impossible to follow the part number change indicated in Revision 1 of the service bulletins and notes that because it tracks the base module, it can ignore the top assembly module part number. The commenter also states that Boeing agrees that Japan Airlines does not need to perform Revision 1 of the service bulletins because the changes to the bulletin caused by Revision 1 do not affect Japan Airlines’ fleet/units. We disagree with removing the reference to Boeing Alert Service Bulletins 747–33A2280 and 767– 33A0087, both Revision 1. We acknowledge that each operator may wish to use different parts and have its own tracking methods. However, we cannot accommodate every operator’s differences in each AD. We have determined that the best way to handle such circumstances is for operators to request an alternative method of compliance (AMOC) in accordance with paragraph (p) of this AD, rather than increasing the complexity of the AD by addressing each operator’s unique situation. We have not revised this AD in this regard. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 2,511 airplanes of the affected designs in the worldwide fleet. This AD affects about 934 airplanes of U.S. registry. The inspection of switches takes about 8 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the inspection for U.S. operators is $597,760, or $640 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 E:\FR\FM\24JAR1.SGM 24JAR1

Agencies

[Federal Register Volume 73, Number 16 (Thursday, January 24, 2008)]
[Rules and Regulations]
[Pages 4063-4066]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-970]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29170; Directorate Identifier 2007-NM-075-AD; 
Amendment 39-15345; AD 2008-02-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319 and A320 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:

    Some taperlocks used in the wing-to-fuselage junction at rib 1 
were found to be non-compliant with the applicable specification, 
resulting in a loss of pre-tension in the fasteners. In such 
conditions, the structural integrity of the aircraft could be 
affected.

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

DATES: This AD becomes effective February 28, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 28, 
2008.

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 Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; 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 September 13, 2007 
(72 FR 52309). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    Some taperlocks used in the wing-to-fuselage junction at rib 1 
were found to be non-compliant with the applicable specification, 
resulting in a loss of pre-tension in the fasteners. In such 
conditions, the structural integrity of the aircraft could be 
affected.
    This Airworthiness Directive mandates a repetitive internal 
inspection of the lower stiffeners, and a repetitive external 
inspection of the lower panels in center and outer wing box at level 
of rib 1 junction.

The corrective action includes contacting Airbus for repair 
instructions and repair 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 considered the comments received.

Request To Refer to Revised Service Information

    The Air Transport Association (ATA), on behalf of one of its 
members, United Airlines, and Airbus ask that we refer to Airbus 
Service Bulletins A320-57-1129 and A320-57-1130, both Revision 02, both 
dated July 17, 2007, for accomplishing the specified actions.
    We agree with the requests to refer to Revision 02 of Airbus 
Service Bulletins A320-57-1129 and A320-57-1130. In the NPRM, we 
referred to Airbus Service Bulletins A320-57-1129, and A320-57-1130, 
both Revision 01, both dated July 28, 2006, as the appropriate sources 
of service information for accomplishing the required actions. Revision 
02 of the service bulletins updates the operator and aircraft 
effectivity to show the latest information. No additional work is 
required by these revisions of the service bulletins. We have changed 
paragraphs (f)(1) and (f)(2) of this AD to refer to Revision 02 of the 
service bulletins. We have also changed paragraphs (f)(1) and (f)(2) to 
give credit to operators that have done the actions previously in 
accordance with Revision 01 of the service bulletins. We have also 
revised the sentence giving credit for an earlier service bulletin in 
paragraph (f)(2) of this AD for clarity.

Request To Allow Installation of a Pin and Sleeve Fastener

    ATA, on behalf of one of its members, Northwest Airlines (NWA), 
states that installation of a pin-and-sleeve fastener, instead of the 
taperlok fastener, should be allowed due to the practical difficulties 
in accomplishing the NPRM

[[Page 4064]]

as currently written. NWA notes that installation of the taperlok 
fasteners requires precision drilling and reaming of the tapered hole 
and countersink, and adds that industry data show that the installation 
of a MIL-B-85667 pin-and-sleeve fastener can be installed by 
conventional manual drilling and reaming of a standard hole with 
relative simplicity and still maintain the fatigue strength capability 
of the taperlok fastener. NWA adds that the fastener capability 
properties of the MIL-B-85667 pin-and-sleeve fastener (titanium tapered 
pin and aluminum sleeve) meet or exceed those of the Airbus taperlok 
fasteners for tensile, shear, and fatigue strength. NWA provided a 
table that identifies the fastener properties.
    We do not agree with the commenters' request. The commenters have 
not provided sufficient data to demonstrate that this installation 
would adequately address the identified unsafe condition. Although the 
MIL-B-85667 pin-and-sleeve fastener material properties may be equal to 
or better than the taperlok fasteners, there are other considerations 
in selection of fasteners that must be addressed, in addition to proper 
drilling and reaming of the tapered hole and countersink. Therefore, we 
have not changed the AD in this regard. However, any operator may 
request an alternative method of compliance (AMOC) in accordance with 
the procedures in paragraph (g) of the AD, provided that sufficient 
data are submitted to substantiate that the proposed AMOC would provide 
an acceptable level of safety.

Conclusion

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

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 583 products of U.S. registry. 
We also estimate that it would take about between 16 and 77 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 the AD on U.S. operators to be between $746,240 
and $3,591,280, or between $1,280 and $6,160 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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:

2008-02-15 Airbus: Amendment 39-15345. Docket No. FAA-2007-29170; 
Directorate Identifier 2007-NM-075-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
28, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A319 and A320 series 
airplanes, certificated in any category, all certified models, all 
serial numbers (MSN); except airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD. Model A320 series airplanes MSN 2164 
through MSN 2688 that have partially received Airbus Modification 
33421 in production are affected by the requirements of this AD.
    (1) Model A319 series airplanes that have received Airbus 
Modifications 28238, 28162, and 28342 in production, or Airbus 
Modification 33421 in production.
    (2) Model A320 series airplanes that have received Airbus 
Modification 33421 fully embodied in production.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

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

[[Page 4065]]

    Some taperlocks used in the wing-to-fuselage junction at rib 1 
were found to be non-compliant with the applicable specification, 
resulting in a loss of pre-tension in the fasteners. In such 
conditions, the structural integrity of the aircraft could be 
affected.
    This Airworthiness Directive mandates a repetitive internal 
inspection of the lower stiffeners, and a repetitive external 
inspection of the lower panels in center and outer wing box at level 
of rib 1 junction.

The corrective action includes contacting Airbus for repair 
instructions and repair if any crack is found.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) For A320-200 aircraft: Before the defined threshold or 
within the defined grace period after the effective date of this AD, 
whichever occurs later, as listed in paragraph 1.E., ``Compliance,'' 
of Airbus Service Bulletin A320-57-1129, Revision 02, dated July 17, 
2007, and following the instructions given in the service bulletin, 
perform an internal ultrasonic inspection of the lower stiffeners in 
the center and outer wing box at the level of the rib 1 junction to 
detect cracks, and if any crack is found, before further flight 
contact Airbus for repair instructions and repair. Repeat this 
inspection at the intervals defined in paragraph 1.E., 
``Compliance,'' of the service bulletin. Actions done before the 
effective date of this AD in accordance with Airbus Service Bulletin 
A320-57-1129, Revision 01, dated July 28, 2006, are acceptable for 
compliance with the corresponding actions of this paragraph.
    (2) For all aircraft: Before the defined threshold or within the 
defined grace period after the effective date of this AD, whichever 
occurs later, as listed in paragraph 1.E., ``Compliance,'' of Airbus 
Service Bulletin A320-57-1130, Revision 02, dated July 17, 2007, and 
following the instructions given in the service bulletin, perform an 
external ultrasonic inspection of the lower stiffeners in the center 
and outer wing box at the level of the rib 1 junction to detect 
cracks, and if any crack is found, before further flight contact 
Airbus for repair instructions and repair. Repeat this inspection at 
the intervals defined in paragraph 1.E., ``Compliance,'' of the 
service bulletin. Actions done before the effective date of this AD 
in accordance with Airbus Service Bulletin A320-57-1130, dated 
September 10, 2004; or Revision 01, dated July 28, 2006; are 
acceptable for compliance with the corresponding actions of this 
paragraph.
    (3) Modification of the aircraft in accordance with the 
instructions contained in Airbus Service Bulletins A320-57-1131, 
A320-57-1137, or A320-57-1140, all dated November 21, 2006; 
terminates the repetitive inspection requirements of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows:
    (1) Although the MCAI or service information does not specify a 
compliance time for corrective action (repair of cracks), paragraphs 
(f)(1) and (f)(2) of this AD require that the corrective action be 
done before further flight.

    (2) Although the MCAI and/or service information specify a 
compliance time for accomplishing the inspections after the 
effective date of the MCAI, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

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 Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2141; 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 EASA Airworthiness Directive 2007-0067R1, 
dated June 7, 2007; and Airbus Service Bulletins A320-57-1129 and 
A320-57-1130, both Revision 02, both dated July 17, 2007; for 
related information.

Material Incorporated by Reference

    (i) You must use the Airbus 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                       Revision                               Date
----------------------------------------------------------------------------------------------------------------
A320-57-1129, including Appendix 01...  02.................................  July 17, 2007.
A320-57-1130, including Appendix 01...  02.................................  July 17, 2007.
A320-57-1131, including Appendix 01     Original...........................  November 21, 2006.
 and excluding Appendix 02.
A320-57-1137, including Appendix 01     Original...........................  November 21, 2006.
 and excluding Appendix 02.
A320-57-1140, including Appendix 01     Original...........................  November 21, 2006.
 and excluding Appendix 02.
----------------------------------------------------------------------------------------------------------------



[[Page 4066]]

    Issued in Renton, Washington, on January 14, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E8-970 Filed 1-23-08; 8:45 am]
BILLING CODE 4910-13-P
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