Airworthiness Directives; Airbus Model A340-211, -212, -311, and -312 Airplanes, 31171-31174 [E7-10754]

Download as PDF 31171 Rules and Regulations Federal Register Vol. 72, No. 108 Wednesday, June 6, 2007 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28354; Directorate Identifier 2006–NM–245–AD; Amendment 39–15086; AD 2007–12–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A340–211, –212, –311, and –312 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. rmajette on PROD1PC64 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Airbus Model A340–211, –212, –311, and –312 airplanes. The existing AD currently requires an initial rotating probe inspection and initial and repetitive ultrasonic inspections for discrepancies of the first fastener hole of the horizontal flange of the keel beam on previously modified airplanes, installation of new fasteners, and corrective action if necessary. This AD retains the actions required by the existing AD and adds new rotating probe inspections and a terminating action for the repetitive inspections of the existing AD. This AD results from a report that certain inspections, done before accomplishing the modification of the lower keel beam fitting and forward lower shell connection, revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. We are issuing this AD to prevent discrepancies of the fastener holes of the horizontal flange of the keel beam, which could result in reduced structural integrity of the fuselage. VerDate Aug<31>2005 15:16 Jun 05, 2007 Jkt 211001 This AD becomes effective June 21, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 21, 2007. On October 27, 2005 (70 FR 59233, October 12, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A340–57–4087, including Appendix 01, dated November 21, 2003. We must receive comments on this AD by August 6, 2007. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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: DATES: Discussion On September 28, 2005, the FAA issued AD 2005–20–27, amendment 39– 14324 (70 FR 59233, October 12, 2005). That AD applies to certain Airbus Model A340–211, –212, –311, and –312 airplanes. That AD requires an initial rotating probe inspection and initial and repetitive ultrasonic inspections for discrepancies of the first fastener hole of the horizontal flange of the keel beam on previously modified airplanes, installation of new fasteners, and PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 corrective action if necessary. That AD resulted from a report that certain inspections done before accomplishing the modification of the lower keel beam fitting and forward lower shell connection revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. The actions specified in that AD are intended to find and fix discrepancies of the fastener holes of the horizontal flange of the keel beam, which could result in reduced structural integrity of the fuselage. Actions Since AD Was Issued Since we issued that AD, further manufacturer analysis of the keel beam/ center wing box (CWB) interface determined that cold working of additional fastener holes and modifications of the CWB lower panel/ keel beam interface was needed to adequately ensure structural integrity of the airplane. These modifications would provide terminating action for the repetitive inspections required by the existing AD. Relevant Service Information Airbus has issued Service Bulletin A340–57–4099, dated March 27, 2006. The service bulletin describes procedures for disconnecting one fastener from the keel beam/bottom skin panel junction by reaming a hole in the keel beam and oversizing fastener 5 of the CWB lower panel, and for coldworking two adjacent fastener holes of the CWB lower panel to install interference fit fasteners. These modifications include rotating probe inspections, if applicable. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. We have also reviewed Airbus Service Bulletin A340–57–4087, Revision 01, including Appendix 01, dated February 15, 2005. (Service Bulletin A340–57– 4087, including Appendix 01, dated November 21, 2003, was cited as the appropriate source of service information in AD 2005–20–27.) Revision 01 is technically the same as the original issue; revisions were made only to the effectivity and certain descriptive paragraphs. The European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Union, E:\FR\FM\06JNR1.SGM 06JNR1 31172 Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules and Regulations mandated the service information and issued airworthiness directive 2006– 0314, dated October 13, 2006, to ensure the continued airworthiness of these airplanes in the European Union. Therefore, we have revised paragraph (h) of this AD to specify making repairs using a method approved by either the FAA, the DGAC (or its delegated agent), or the EASA (or its delegated agent). FAA’s Determination and Requirements of This AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are issuing this AD to supersede AD 2005–20–27. This new AD retains the requirements of the existing AD. This AD also requires accomplishing the actions specified in Service Bulletin A340–57–4099, described previously, except as discussed under ‘‘Difference Between AD and Service Bulletin A340–57– 4099.’’ Costs of Compliance None of the airplanes affected by this action are on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future. For any affected airplane imported and placed on the U.S. Register in the future, the estimated costs to accomplish the specified actions, at an average labor rate of $80 per work hour, are as follows: For the actions required by AD 2005– 20–27 and retained by this AD: It takes between 3 and 8 work hours per airplane for the initial inspections and about 2 work hours per airplane for each repetitive inspection. Parts cost $190 for each kit; two kits are required for installing the new fasteners. Based on these figures, the estimated cost of the initial actions is between $620 and $1,020 per airplane; and the estimated cost of the repeat inspection is $160 per airplane, per inspection cycle. For the new actions required by this AD: It takes between 14 and 29 work hours per airplane to do the inspections and modifications. Parts cost between $1,250 and $1,680 per kit. Based on these figures, the estimated cost of these actions is between $2,370 and $4,000 per airplane. rmajette on PROD1PC64 with RULES Difference Between AD and Service Bulletin A340–57–4099 Service Bulletin A340–57–4099 specifies contacting the manufacturer for disposition of certain repair conditions; however, this AD would require the repair of those conditions to be accomplished per a method approved by either the FAA or the EASA (or its delegated agent). In light of the type of repair that would be required to address the identified unsafe condition, and in consonance with existing bilateral airworthiness agreements, the FAA has determined that, for this AD, a repair approved by either the FAA or the EASA (or its delegated agent) would be acceptable for compliance with the requirements of paragraph (j) of this AD. Explanation of Change Made to Requirements of Existing AD Paragraph (h) of the existing AD specifies making repairs using a method approved by the FAA or the Direction Generale De L’Aviation Civile (DGAC) (or its delegated agent). The European Aviation Safety Agency (EASA) has assumed responsibility for the airplane models that would be subject to this AD. VerDate Aug<31>2005 15:16 Jun 05, 2007 Jkt 211001 FAA’s Determination of the Effective Date No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in less than 30 days after it is published in the Federal Register. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28354; Directorate Identifier 2006–NM–245–AD’’ at the beginning of PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http://dms.dot.gov. Examining the Docket You may examine the 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 the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. 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 E:\FR\FM\06JNR1.SGM 06JNR1 Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules and Regulations the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this 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 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 39–14324 (70 FR 59233, October 12, 2005) and adding the following new airworthiness directive (AD): I 2007–12–08 Airbus: Amendment 39–15086. Docket No. FAA–2007–28354; Directorate Identifier 2006–NM–245–AD. Effective Date (a) This AD becomes effective June 21, 2007. rmajette on PROD1PC64 with RULES Affected ADs (b) This AD supersedes AD 2005–20–27. Applicability (c) This AD applies to Airbus Model A340– 211, –212, –311, and –312 airplanes, certificated in any category; serial numbers 0006, 0007 (right-hand side of the airplane only), 0008 (left-hand side only), 0013, 0020, 0024 (left-hand side only), 0027 through 0029 inclusive, 0031, 0033, 0035, 0038 through 0040 inclusive, 0043, 0047, 0049, and 0052. Unsafe Condition (d) This AD results from a report that certain inspections, done before VerDate Aug<31>2005 15:16 Jun 05, 2007 Jkt 211001 accomplishing the modification of the lower keel beam fitting and forward lower shell connection, revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. We are issuing this AD to prevent discrepancies of the fastener holes of the horizontal flange of the keel beam, 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. Restatement of Requirements of AD 2005– 20–27 Initial/Repetitive Nondestructive Test Inspections/Repair (f) Within 5,420 flight cycles or 26,200 flight hours after accomplishing Airbus Modification 43577, whichever is first: Perform an initial rotating probe inspection for discrepancies of the first fastener hole of the horizontal flange of the keel beam by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–57–4087, dated November 21, 2003; or Revision 01, dated February 15, 2005. If no cracking is found, before further flight, inspect for correct fastener diameter tolerance; if the fastener diameter is out of tolerance, before further flight, ream to oversize the fastener holes and install oversize fasteners in accordance with the Accomplishment Instructions of the service bulletin. Accomplishing the modifications specified in paragraph (i) of this AD ends the requirement for these inspections. (g) If no cracking is found during any inspection required by paragraph (f) of this AD: Within 1,480 flight cycles or 7,400 flight hours, whichever is first, after accomplishing the inspection, perform an initial ultrasonic inspection for discrepancies of the first fastener hole of the horizontal flange of the keel beam by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 57–4087, dated November 21, 2003; or Revision 01, dated February 15, 2005. If no cracking is found, repeat the ultrasonic inspection thereafter at intervals not to exceed 1,480 flight cycles or 7,400 flight hours, whichever is first; until the modifications required by paragraph (i) of this AD are accomplished. Repair Per the FAA; the Direction Generale De L’Aviation Civile (DGAC); or the European Aviation Safety Agency (EASA) (h) If any cracking is found during any inspection required by this AD: Before further flight, repair per 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). Within 1,480 flight cycles or 7,400 flight hours, whichever is first, after repair of any cracking, perform an ultrasonic inspection as required by paragraph (g) of this AD. Repeat the ultrasonic inspection thereafter at intervals PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 31173 not to exceed 1,480 flight cycles or 7,400 flight hours, whichever is first; until the actions required by paragraph (i) of this AD are accomplished. New Requirements of This AD Modifications (i) Within 118 months after the effective date of this AD: Disconnect the keel beam from the center wing box panel at fastener hole 5, do applicable rotating probe inspections, and do cold work and install interference fit fasteners in two adjacent fastener holes of the center wing box panel; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 57–4099, dated March 27, 2006, except as required by paragraph (j) of this AD. Accomplishing these actions terminates the inspection requirements of paragraphs (f), (g), and (h) of this AD. Repair (j) If any crack is found during any action required by paragraph (i) of this AD and Service Bulletin A340–57–4099 specifies to contact Airbus: Before further flight, repair per a method approved by the Manager, International Branch, ANM–116; the DGAC (or its delegated agent); or the EASA (or its delegated agent). No Reporting Required (k) Although Airbus Service Bulletin A340–57–4087, dated November 21, 2003; and Revision 01, dated February 15, 2005, specify submitting an inspection report to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (l)(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) 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. Related Information (m) The European Aviation Safety Agency airworthiness directive 2006–0314, dated October 13, 2006, also addresses the subject of this AD. Material Incorporated by Reference (n) You must use Airbus Service Bulletin A340–57–4099, dated March 27, 2006; Airbus Service Bulletin A340–57–4087, including Appendix 01, dated November 21, 2003, and Airbus Service Bulletin A340–57– 4087, Revision 01, excluding Appendix 01, dated February 15, 2005; 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 A340–57–4099, E:\FR\FM\06JNR1.SGM 06JNR1 31174 Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules and Regulations dated March 27, 2006; and Airbus Service Bulletin A340–57–4087, Revision 01, excluding Appendix 01, dated February 15, 2005; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On October 27, 2005 (70 FR 59233, October 12, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A340– 57–4087, including Appendix 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 NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Renton, Washington, on May 25, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10754 Filed 6–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25738; Directorate Identifier 2006–NE–27–AD; Amendment 39– 15085; AD 2007–12–07] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) CF6–80C2B Series Turbofan Engines Examining the AD Docket Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. rmajette on PROD1PC64 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE CF6–80C2B series turbofan engines with electronic control units (ECUs), installed on Boeing 747 and 767 series airplanes. This AD requires installing software version 8.2.Q1 to the engine ECU, which increases the engine’s margin to flameout. This AD results from reports of engine flameout events during flight, including reports of events where all engines simultaneously experienced a flameout or other adverse operation. Though the root cause investigation is not yet complete, we believe exposure to ice crystals during flight is associated with these flameout events. We are issuing this AD to provide increased margin to flameout, which will minimize the potential of an VerDate Aug<31>2005 15:16 Jun 05, 2007 Jkt 211001 all-engine flameout event caused by ice accretion and shedding during flight. DATES: This AD becomes effective July 11, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of July 11, 2007. ADDRESSES: You can get the service information identified in this AD from General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672–8400, fax (513) 672–8422. You may examine the AD docket on the Internet at http://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: John Golinski, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: john.golinski@faa.gov; telephone: (781) 238–7135, fax: (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF6–80C2B series turbofan engines with ECUs, installed on Boeing 747 and 767 series airplanes. We published the proposed AD in the Federal Register on October 24, 2006 (71 FR 62215). That action proposed to require installing software version 8.2.Q1 to the engine ECU, which increases the engine’s margin to flameout. You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Comment That Corrective Actions Should Be Expanded One commenter, the Airline Pilots Association, International, states that the corrective action should be PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 expanded in this AD to be fully effective. The commenter states that the prescribed modification addresses only the flameout and restart issues, while the problems of engine ice accretion and compressor blade damage due to ice shedding during operations, remain. The commenter states that, due to the severity of single- and dual-engine flameout events, the FAA and GE must examine the engine certification and operating envelope to determine the causes of ice accretions and compressor blade damage while operating in an ice crystal environment and continue to develop a more comprehensive solution. We do not agree. This AD considers the ice accretion location, quantity, and the potential of compressor blade damage caused by impact with ice. Paragraph (f) of this AD states that these AD actions are interim actions due to the on-going investigation, and that we may take further rulemaking actions in the future based on the results of the investigation and field experience. Request To Eliminate Certain Wording Japan Airlines International (JAL) requests that we eliminate ‘‘at the next shop visit of the engine’’ in the compliance section. Doing this would: • Then allow operators to accomplish the retrofit program on Boeing 767 series airplanes more aggressively; and • Would facilitate completing the program in the proposed 5-year compliance period, without causing aircraft on the ground (AOG) situations, due to a shortage of spare ECUs. JAL is concerned that there might be a shortage of spare ECUs that could result in grounded aircraft. JAL provided information and data on their planned retrofit for their fleet of Boeing 767 and 747 series airplanes. We partially agree. Eliminating the proposed wording would result in a less aggressive replacement program for the total population of engines. JAL did not provide any supporting data of how this change would result in a more aggressive compliance program for engines installed on the Boeing 767 airplanes. Our risk assessment indicates that the risk presented by this unsafe condition can be successfully managed within the current and expected parts availability. Therefore, we did not change the AD. In reviewing JAL’s comment, we noted that our intent could be clarified. We changed the AD to clarify that ECUs installed with previous versions of software can be installed on an engine for a period of time. The added paragraph in the AD discusses two possible conditions: (1) Reverting to previous versions of E:\FR\FM\06JNR1.SGM 06JNR1

Agencies

[Federal Register Volume 72, Number 108 (Wednesday, June 6, 2007)]
[Rules and Regulations]
[Pages 31171-31174]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10754]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules 
and Regulations

[[Page 31171]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28354; Directorate Identifier 2006-NM-245-AD; 
Amendment 39-15086; AD 2007-12-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A340-211, -212, -311, and 
-312 Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to certain Airbus Model A340-211, -212, -311, and -
312 airplanes. The existing AD currently requires an initial rotating 
probe inspection and initial and repetitive ultrasonic inspections for 
discrepancies of the first fastener hole of the horizontal flange of 
the keel beam on previously modified airplanes, installation of new 
fasteners, and corrective action if necessary. This AD retains the 
actions required by the existing AD and adds new rotating probe 
inspections and a terminating action for the repetitive inspections of 
the existing AD. This AD results from a report that certain 
inspections, done before accomplishing the modification of the lower 
keel beam fitting and forward lower shell connection, revealed cracking 
that was outside the modification limits specified in the service 
bulletin; the cracking was repaired by installing a titanium doubler. 
We are issuing this AD to prevent discrepancies of the fastener holes 
of the horizontal flange of the keel beam, which could result in 
reduced structural integrity of the fuselage.

DATES: This AD becomes effective June 21, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of June 21, 2007.
    On October 27, 2005 (70 FR 59233, October 12, 2005), the Director 
of the Federal Register approved the incorporation by reference of 
Airbus Service Bulletin A340-57-4087, including Appendix 01, dated 
November 21, 2003.
    We must receive comments on this AD by August 6, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    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:

Discussion

    On September 28, 2005, the FAA issued AD 2005-20-27, amendment 39-
14324 (70 FR 59233, October 12, 2005). That AD applies to certain 
Airbus Model A340-211, -212, -311, and -312 airplanes. That AD requires 
an initial rotating probe inspection and initial and repetitive 
ultrasonic inspections for discrepancies of the first fastener hole of 
the horizontal flange of the keel beam on previously modified 
airplanes, installation of new fasteners, and corrective action if 
necessary. That AD resulted from a report that certain inspections done 
before accomplishing the modification of the lower keel beam fitting 
and forward lower shell connection revealed cracking that was outside 
the modification limits specified in the service bulletin; the cracking 
was repaired by installing a titanium doubler. The actions specified in 
that AD are intended to find and fix discrepancies of the fastener 
holes of the horizontal flange of the keel beam, which could result in 
reduced structural integrity of the fuselage.

Actions Since AD Was Issued

    Since we issued that AD, further manufacturer analysis of the keel 
beam/center wing box (CWB) interface determined that cold working of 
additional fastener holes and modifications of the CWB lower panel/keel 
beam interface was needed to adequately ensure structural integrity of 
the airplane. These modifications would provide terminating action for 
the repetitive inspections required by the existing AD.

Relevant Service Information

    Airbus has issued Service Bulletin A340-57-4099, dated March 27, 
2006. The service bulletin describes procedures for disconnecting one 
fastener from the keel beam/bottom skin panel junction by reaming a 
hole in the keel beam and oversizing fastener 5 of the CWB lower panel, 
and for cold-working two adjacent fastener holes of the CWB lower panel 
to install interference fit fasteners. These modifications include 
rotating probe inspections, if applicable. Accomplishing the actions 
specified in the service information is intended to adequately address 
the unsafe condition.
    We have also reviewed Airbus Service Bulletin A340-57-4087, 
Revision 01, including Appendix 01, dated February 15, 2005. (Service 
Bulletin A340-57-4087, including Appendix 01, dated November 21, 2003, 
was cited as the appropriate source of service information in AD 2005-
20-27.) Revision 01 is technically the same as the original issue; 
revisions were made only to the effectivity and certain descriptive 
paragraphs.
    The European Aviation Safety Agency (EASA), which is the 
airworthiness authority for the European Union,

[[Page 31172]]

mandated the service information and issued airworthiness directive 
2006-0314, dated October 13, 2006, to ensure the continued 
airworthiness of these airplanes in the European Union.

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States. Therefore, we are issuing this AD to 
supersede AD 2005-20-27. This new AD retains the requirements of the 
existing AD. This AD also requires accomplishing the actions specified 
in Service Bulletin A340-57-4099, described previously, except as 
discussed under ``Difference Between AD and Service Bulletin A340-57-
4099.''

Difference Between AD and Service Bulletin A340-57-4099

    Service Bulletin A340-57-4099 specifies contacting the manufacturer 
for disposition of certain repair conditions; however, this AD would 
require the repair of those conditions to be accomplished per a method 
approved by either the FAA or the EASA (or its delegated agent). In 
light of the type of repair that would be required to address the 
identified unsafe condition, and in consonance with existing bilateral 
airworthiness agreements, the FAA has determined that, for this AD, a 
repair approved by either the FAA or the EASA (or its delegated agent) 
would be acceptable for compliance with the requirements of paragraph 
(j) of this AD.

Explanation of Change Made to Requirements of Existing AD

    Paragraph (h) of the existing AD specifies making repairs using a 
method approved by the FAA or the Direction Generale De L'Aviation 
Civile (DGAC) (or its delegated agent). The European Aviation Safety 
Agency (EASA) has assumed responsibility for the airplane models that 
would be subject to this AD. Therefore, we have revised paragraph (h) 
of this AD to specify making repairs using a method approved by either 
the FAA, the DGAC (or its delegated agent), or the EASA (or its 
delegated agent).

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future. For any affected airplane imported and placed on the U.S. 
Register in the future, the estimated costs to accomplish the specified 
actions, at an average labor rate of $80 per work hour, are as follows:
    For the actions required by AD 2005-20-27 and retained by this AD: 
It takes between 3 and 8 work hours per airplane for the initial 
inspections and about 2 work hours per airplane for each repetitive 
inspection. Parts cost $190 for each kit; two kits are required for 
installing the new fasteners. Based on these figures, the estimated 
cost of the initial actions is between $620 and $1,020 per airplane; 
and the estimated cost of the repeat inspection is $160 per airplane, 
per inspection cycle.
    For the new actions required by this AD: It takes between 14 and 29 
work hours per airplane to do the inspections and modifications. Parts 
cost between $1,250 and $1,680 per kit. Based on these figures, the 
estimated cost of these actions is between $2,370 and $4,000 per 
airplane.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2007-
28354; Directorate Identifier 2006-NM-245-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of that Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you may visit 
http://dms.dot.gov.

Examining the Docket

    You may examine the 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 the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

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

[[Page 31173]]

the States, on the relationship between the national government and the 
States, or on the distribution of power and responsibilities among the 
various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this 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:

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 39-14324 (70 FR 59233, October 12, 2005) and adding 
the following new airworthiness directive (AD):

2007-12-08 Airbus: Amendment 39-15086. Docket No. FAA-2007-28354; 
Directorate Identifier 2006-NM-245-AD.

Effective Date

    (a) This AD becomes effective June 21, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-20-27.

Applicability

    (c) This AD applies to Airbus Model A340-211, -212, -311, and -
312 airplanes, certificated in any category; serial numbers 0006, 
0007 (right-hand side of the airplane only), 0008 (left-hand side 
only), 0013, 0020, 0024 (left-hand side only), 0027 through 0029 
inclusive, 0031, 0033, 0035, 0038 through 0040 inclusive, 0043, 
0047, 0049, and 0052.

Unsafe Condition

    (d) This AD results from a report that certain inspections, done 
before accomplishing the modification of the lower keel beam fitting 
and forward lower shell connection, revealed cracking that was 
outside the modification limits specified in the service bulletin; 
the cracking was repaired by installing a titanium doubler. We are 
issuing this AD to prevent discrepancies of the fastener holes of 
the horizontal flange of the keel beam, 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.

Restatement of Requirements of AD 2005-20-27

Initial/Repetitive Nondestructive Test Inspections/Repair

    (f) Within 5,420 flight cycles or 26,200 flight hours after 
accomplishing Airbus Modification 43577, whichever is first: Perform 
an initial rotating probe inspection for discrepancies of the first 
fastener hole of the horizontal flange of the keel beam by doing all 
the actions in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A340-57-4087, dated November 21, 2003; or 
Revision 01, dated February 15, 2005. If no cracking is found, 
before further flight, inspect for correct fastener diameter 
tolerance; if the fastener diameter is out of tolerance, before 
further flight, ream to oversize the fastener holes and install 
oversize fasteners in accordance with the Accomplishment 
Instructions of the service bulletin. Accomplishing the 
modifications specified in paragraph (i) of this AD ends the 
requirement for these inspections.
    (g) If no cracking is found during any inspection required by 
paragraph (f) of this AD: Within 1,480 flight cycles or 7,400 flight 
hours, whichever is first, after accomplishing the inspection, 
perform an initial ultrasonic inspection for discrepancies of the 
first fastener hole of the horizontal flange of the keel beam by 
doing all the actions in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A340-57-4087, dated November 
21, 2003; or Revision 01, dated February 15, 2005. If no cracking is 
found, repeat the ultrasonic inspection thereafter at intervals not 
to exceed 1,480 flight cycles or 7,400 flight hours, whichever is 
first; until the modifications required by paragraph (i) of this AD 
are accomplished.

Repair Per the FAA; the Direction Generale De L'Aviation Civile (DGAC); 
or the European Aviation Safety Agency (EASA)

    (h) If any cracking is found during any inspection required by 
this AD: Before further flight, repair per 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). Within 1,480 flight cycles or 7,400 flight 
hours, whichever is first, after repair of any cracking, perform an 
ultrasonic inspection as required by paragraph (g) of this AD. 
Repeat the ultrasonic inspection thereafter at intervals not to 
exceed 1,480 flight cycles or 7,400 flight hours, whichever is 
first; until the actions required by paragraph (i) of this AD are 
accomplished.

New Requirements of This AD

Modifications

    (i) Within 118 months after the effective date of this AD: 
Disconnect the keel beam from the center wing box panel at fastener 
hole 5, do applicable rotating probe inspections, and do cold work 
and install interference fit fasteners in two adjacent fastener 
holes of the center wing box panel; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-57-4099, 
dated March 27, 2006, except as required by paragraph (j) of this 
AD. Accomplishing these actions terminates the inspection 
requirements of paragraphs (f), (g), and (h) of this AD.

Repair

    (j) If any crack is found during any action required by 
paragraph (i) of this AD and Service Bulletin A340-57-4099 specifies 
to contact Airbus: Before further flight, repair per a method 
approved by the Manager, International Branch, ANM-116; the DGAC (or 
its delegated agent); or the EASA (or its delegated agent).

No Reporting Required

    (k) Although Airbus Service Bulletin A340-57-4087, dated 
November 21, 2003; and Revision 01, dated February 15, 2005, specify 
submitting an inspection report to the manufacturer, this AD does 
not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (l)(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) 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.

Related Information

    (m) The European Aviation Safety Agency airworthiness directive 
2006-0314, dated October 13, 2006, also addresses the subject of 
this AD.

Material Incorporated by Reference

    (n) You must use Airbus Service Bulletin A340-57-4099, dated 
March 27, 2006; Airbus Service Bulletin A340-57-4087, including 
Appendix 01, dated November 21, 2003, and Airbus Service Bulletin 
A340-57-4087, Revision 01, excluding Appendix 01, dated February 15, 
2005; 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 A340-57-4099,

[[Page 31174]]

dated March 27, 2006; and Airbus Service Bulletin A340-57-4087, 
Revision 01, excluding Appendix 01, dated February 15, 2005; in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On October 27, 2005 (70 FR 59233, October 12, 2005), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A340-57-4087, including 
Appendix 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 NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 25, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-10754 Filed 6-5-07; 8:45 am]
BILLING CODE 4910-13-P