Airworthiness Directives; Airbus Model A330 Airplanes and Model A340-200 and -300 Series Airplanes, 64881-64884 [E6-18471]

Download as PDF 64881 Rules and Regulations Federal Register Vol. 71, No. 214 Monday, November 6, 2006 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–2005–22812; Directorate Identifier 2005–NM–134–AD; Amendment 39–14811; AD 2006–22–14] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. cprice-sewell on PROD1PC66 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330 airplanes and Model A340–200 and –300 series airplanes. This AD requires repetitive detailed inspections for cracking in the aft web of support rib 6 between certain bottom skin stringers on both wings; high frequency eddy current inspections for cracking of the attachment holes of the fuel pipes, and repair if necessary. This AD also provides for an optional modification, which extends a certain inspection threshold, and mandates, for certain airplanes, a new modification of support rib 6 on both wings, which ends the repetitive inspection requirement. This AD results from a report of significant cracking found in the aft web of support rib 6 on both wings. We are issuing this AD to prevent cracking in the aft web of support rib 6, which could result in overloading of adjacent ribs and the surrounding wing structure and consequent reduced structural integrity of the wing. DATES: This AD becomes effective December 11, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 11, 2006. 15:39 Nov 03, 2006 Tim Backman, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; fax (425) 227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Examining the Docket Airworthiness Directives; Airbus Model A330 Airplanes and Model A340–200 and –300 Series Airplanes VerDate Aug<31>2005 You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for the service information identified in this AD. ADDRESSES: Jkt 211001 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 street address stated in the ADDRESSES section. Discussion The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A330 airplanes and Model A340– 200 and –300 series airplanes. That supplemental NPRM was published in the Federal Register on May 26, 2006 (71 FR 30340). That supplemental NPRM proposed to require repetitive detailed inspections for cracking in the aft web of support rib 6 between certain bottom skin stringers on both wings; high frequency eddy current inspections for cracking of the attachment holes of the fuel pipes, and repair if necessary. The supplemental NPRM also provided for an optional modification, which would extend a certain inspection threshold. For certain airplanes, the supplemental NPRM proposed to require a new modification of support rib 6 on both wings, which would end the repetitive inspection requirement. The supplemental NPRM also proposed to reduce the applicability in the original NPRM. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Comment We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. Request for Credit for Terminating Modification The Air Transport Association (ATA), on behalf of its member Northwest Airlines (NWA), asks that we recognize Airbus Modification 54432 as terminating action for the repetitive inspection requirements in the supplemental NPRM. NWA states that this modification is being incorporated by Airbus in production as the ‘‘production solution’’ for the fatigue cracking problems. NWA adds that the modification will be installed on its Model A330 airplanes delivered with manufacturer’s serial number 0778 and subsequent. We agree that Airbus Modification 54432 will be terminating action for the referenced repetitive inspections. However, that modification is not yet approved by either the European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Union, or the FAA. The modification is currently in the approval process with the EASA. This modification is the production solution that installs a re-designed rib for production airplanes with a new wing build. Once the modification is approved, the referenced EASA airworthiness directive will be revised to include this terminating action. After the modification is approved and available, operators may request an alternative method of compliance for installing the modification. We have not changed the AD in this regard. Explanation of Change to the Supplemental NPRM Airbus Service Bulletins A300–57– 3085 and A340–57–4093, both Revision 02, both dated September 29, 2005, were included in the service information section of the supplemental NPRM as the sources of service information for accomplishing the inspections. However, Revision 02 was inadvertently omitted from paragraph (l) of the supplemental NPRM; we have added Revision 02 to paragraph (l) accordingly. E:\FR\FM\06NOR1.SGM 06NOR1 64882 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations Conclusion We have carefully reviewed the available data, including the comment 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. cprice-sewell on PROD1PC66 with RULES Costs of Compliance This AD affects about 25 airplanes of U.S. registry. The inspections take about 4 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the inspections for U.S. operators is $8,000, or $320 per airplane, per inspection cycle. The modification of support rib 6 on the left-hand wing takes about 38 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost about $5,020 per airplane. Based on these figures, the estimated cost of this modification of the left-hand wing on U.S. operators is $201,500, or $8,060 per airplane. The modification of support rib 6 on the right-hand wing takes about 38 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost about $5,020 per airplane. Based on these figures, the estimated cost of this modification of the righthand wing on U.S. operators is $201,500, or $8,060 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will VerDate Aug<31>2005 15:39 Nov 03, 2006 Jkt 211001 not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I 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 adding the following new airworthiness directive (AD): I 2006–22–14 Airbus: Amendment 39–14811. Docket No. FAA–2005–22812; Directorate Identifier 2005–NM–134–AD. Effective Date (a) This AD becomes effective December 11, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330 airplanes and Model A340–200 and –300 series airplanes, certificated in any category; on which Airbus Modification 41114 or 44599 was done during production; except those airplanes on which Airbus Modification 53883 was done during production. Unsafe Condition (d) This AD results from a report of significant cracking found in the aft web of PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 support rib 6 on both wings. We are issuing this AD to prevent cracking in the aft web of support rib 6, which could result in overloading of adjacent ribs and the surrounding wing structure and consequent reduced structural integrity of the wing. 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. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Repetitive Inspections (f) For Model A330 series airplanes on which Airbus Modification 53882 was not done during production: At the applicable time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, perform a detailed inspection for cracking in the aft web of support rib 6 between bottom skin stringers 18 and 20 on both wings, and high frequency eddy current inspections for cracking of the attachment holes of the fuel pipe and fuel pipe mounting, by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 57–3085, Revision 02, dated September 29, 2005. If no crack is found during the initial inspections, repeat the inspections thereafter at intervals not to exceed 8,000 flight cycles or 25,000 flight hours, whichever is first, until the terminating action specified in paragraph (n) of this AD is done. If any crack is found during any inspection, repair as specified in paragraph (k) of this AD, or before further flight do the terminating action specified in paragraph (n) of this AD. (1) For airplanes that have accumulated 7,999 or fewer total flight cycles, and 24,999 or fewer total flight hours, as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. (i) Before the accumulation of 8,000 total flight cycles or 25,000 total flight hours, whichever is first. (ii) Within 8 months after the effective date of this AD. (2) For airplanes that have accumulated 8,000 or more total flight cycles, but fewer than 10,000 total flight cycles; or 25,000 or more total flight hours, but fewer than 30,000 total flight hours; as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (i) Before the accumulation of 10,000 total flight cycles or 30,000 total flight hours, whichever is first. (ii) Within 8 months after the effective date of this AD. (3) For airplanes that have accumulated 10,000 or more total flight cycles or 30,000 or more total flight hours as of the effective E:\FR\FM\06NOR1.SGM 06NOR1 cprice-sewell on PROD1PC66 with RULES Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations date of this AD: Do the inspections within 3 months after the effective date of this AD. (g) For Model A330 series airplanes on which Airbus Modification 53882 was done during production or on which Airbus Service Bulletin A330–57–3087, dated February 15, 2005, or Revision 01, dated September 22, 2005, has been done: Perform the applicable inspections required by paragraph (f) of this AD at the earliest of the initial inspection thresholds specified in Figure 4, Sheet 1, ‘‘Inspection Flow Chart’’ of Airbus Service Bulletin A330–57–3085, Revision 02, dated September 29, 2005; or within 6 months after the effective date of this AD, whichever is later. Repeat the inspections required by paragraph (f) of this AD at the time specified in paragraph (f) of this AD, until the terminating action specified in paragraph (n) of this AD is done. (h) For Model A340 series airplanes on which Airbus Modification 53882 was not done during production: Perform the inspections required by paragraph (f) of this AD at the applicable time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Perform the inspections by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–57–4093, Revision 02, dated September 29, 2005. Repeat the inspections thereafter at intervals not to exceed 8,000 flight cycles or 30,200 flight hours, whichever is first, until the terminating action specified in paragraph (n) of this AD is done. (1) For airplanes that have accumulated 7,999 or fewer total flight cycles, and 30,199 or fewer total flight hours, as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) Before the accumulation of 8,000 total flight cycles or 30,200 total flight hours, whichever is first. (ii) Within 8 months after the effective date of this AD. (2) For airplanes that have accumulated 8,000 or more total flight cycles, but fewer than 10,000 total flight cycles; or 30,200 or more total flight cycles, but fewer than 43,700 total flight hours, as of the effective date of this AD: Do the inspections at the later of the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) Before the accumulation of 10,000 total flight cycles or 43,700 total flight hours, whichever is first. (ii) Within 8 months after the effective date of this AD. (3) For airplanes that have accumulated 10,000 or more total flight cycles or 43,700 or more total flight hours as of the effective date of this AD: Do the inspections within 3 months after the effective date of this AD. (i) For Model A340 series airplanes on which Airbus Modification 53882 was done during production or on which Airbus Service Bulletin A340–57–4095, dated February 15, 2005, or Revision 01, dated September 22, 2005, has been done: Perform the applicable inspections required by paragraph (f) of this AD at the earliest of the initial inspection thresholds specified in Figure 4, Sheet 1, ‘‘Inspection Flow Chart’’ of Airbus Service Bulletin A340–57–4093, VerDate Aug<31>2005 15:39 Nov 03, 2006 Jkt 211001 Revision 02, dated September 29, 2005; or within 6 months after the effective date of this AD, whichever is later. Repeat the inspections required by paragraph (f) of this AD at the time specified in paragraph (h) of this AD, until the terminating action specified in paragraph (n) of this AD is done. Inspections Accomplished According to Previous Issue of Service Bulletins (j) Inspections accomplished before the effective date of this AD according to Airbus All Operator Telex A330–57A3085 or A340– 57A4093, each dated December 15, 2004; or Airbus Service Bulletin A330–57–3085 or A340–57–4093, each Revision 01, each dated March 25, 2005; are considered acceptable for compliance with the corresponding inspections specified in this AD. Repair (k) If any cracking is found during any inspection required by this AD: Before further flight, either repair and get a schedule for subsequent inspections, according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent); or accomplish the terminating action specified in paragraph (n) of this AD. Optional Modification (l) Accomplishing the modification of the fuel pipe connector and the fastener holes of support rib 6 on both wings by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A330– 57–3087 or A340–57–4095, each dated February 15, 2005, or Revision 01, each dated September 22, 2005, as applicable, extends the interval for the next inspection to the applicable post-modification inspection threshold specified in Figure 4, Sheet 1, ‘‘Inspection Flow Chart’’ of Airbus Service Bulletins A330–57–3085 or A340–57–4093, each Revision 02, each dated September 29, 2005, as applicable. After accomplishing that inspection, repeat the applicable inspections required by paragraph (f) or (h) of this AD at the applicable repetitive inspection interval specified in Figure 4 of the Accomplishment Instructions of the applicable service bulletin, until the terminating action specified in paragraph (n) of this AD is done. Hard or Overweight Landing (m) For Model A330 series airplanes with 8,000 or more total flight cycles or 25,000 or more total flight hours, and Model A340 series airplanes with 8,000 or more total flight cycles or 30,200 or more total flight hours that have not been modified in accordance with paragraph (n) of this AD: Before further flight after any hard or overweight landing of the airplane, accomplish the applicable follow-on inspections and any applicable corrective actions according to a method approved by either the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). Accomplishing the inspections in Chapter 05–51–11, titled ‘‘Inspection After Hard/Overweight Landing—Inspection/ Check,’’ dated April 1, 2005, or July 1, 2006, of the Airbus A330 Aircraft Maintenance PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 64883 Manual (AMM); or Chapter 05–51–11, titled ‘‘Inspection After Hard/Overweight Landing—Inspection/Check,’’ dated July 1, 2006, of the Airbus A340 AMM; as applicable; and Airbus A330/A340 Technical Disposition (TD) TD/J1/S3/00608/2005, Issue C, dated April 26, 2005, titled ‘‘Inspections following hard landing, both wings,’’ are approved methods. Operators can obtain the TD from Airbus. Terminating Modification (n) For airplanes on which support rib 6 on both wings has not been repaired in accordance with paragraph (k) of this AD: Within 60 months after the effective date of this AD, modify the fuel pipe connector and the fastener holes of support rib 6 on both wings by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A330–57–3088 or A340–57– 4096, each including Appendix 01, each dated September 21, 2005, as applicable. Accomplishing the modification in this paragraph ends the repetitive inspections required by this AD. Repair of support rib 6 on both wings before the effective date of this AD using Airbus A330/A340 Repair Instruction R572–57023, Issue D, dated May 11, 2005; or R572–57026, Issue C, dated December 2005; as applicable, ends the repetitive inspections required by this AD. Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (p) French airworthiness directives F– 2006–008 and F–2006–009, both dated January 4, 2006, also address the subject of this AD. Material Incorporated by Reference (q) You must use the applicable Airbus service bulletins specified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. E:\FR\FM\06NOR1.SGM 06NOR1 64884 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin Revision level Date A330–57–3085 .................................................................................................................................... A330–57–3087 .................................................................................................................................... A330–57–3087 .................................................................................................................................... A330–57–3088, including Appendix 01 .............................................................................................. A340–57–4093 .................................................................................................................................... A340–57–4095 .................................................................................................................................... A340–57–4095 .................................................................................................................................... A340–57–4096, including Appendix 01 .............................................................................................. 02 ............................. Original .................... 01 ............................. Original .................... 02 ............................. Original .................... 01 ............................. Original .................... September 29, 2005. February 15, 2005. September 22, 2005. September 21, 2005. September 29, 2005. February 15, 2005. September 22, 2005. September 21, 2005. Issued in Renton, Washington, on October 25, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–18471 Filed 11–3–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23921; Directorate Identifier 2005–NM–205–AD; Amendment 39–14812; AD 2006–22–15] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 747 series airplanes. That AD currently requires repetitive inspections for cracking of the top and side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. This new AD reduces the interval for certain repetitive inspections and removes a certain optional inspection. This new AD also requires replacing the NWW side and top panels with new panels, which terminates the repetitive inspections. This AD results from the development of a new modification. We are issuing this AD to prevent fatigue cracks in the top and side panel webs and stiffeners of the NWW, which could compromise the structural integrity of the NWW and could lead to the rapid decompression of the airplane. DATES: This AD becomes effective December 11, 2006. The Director of the Federal Register approved the incorporation by reference cprice-sewell on PROD1PC66 with RULES SUMMARY: VerDate Aug<31>2005 15:39 Nov 03, 2006 Jkt 211001 of a certain publication listed in the AD as of December 11, 2006. On May 10, 2005 (70 FR 21141, April 25, 2005), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2465, Revision 4, dated February 24, 2005. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Nick Kusz, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6432; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2005–09–02, amendment 39–14070 (70 FR 21141, April 25, 2005). [A correction of that AD was published in the Federal Register on May 25, 2005 (70 FR 29940).] The existing AD applies to all Boeing Model 747 series airplanes. That NPRM was published in the Federal Register on February 15, 2006 (71 FR 7883). That NPRM proposed to continue to require repetitive inspections for cracking of the top and PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. That NPRM also proposed to reduce the interval for certain repetitive inspections and remove a certain optional inspection. That NPRM also proposed to require replacing the NWW side and top panels with new panels, which would terminate the repetitive inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Support for the NPRM Boeing, the airplane manufacturer, agrees with the contents of the NPRM. Request To Remove Actions for Group 2 Airplanes or Extend Compliance Time The Air Transport Association (ATA), on behalf of one of its members, Northwest Airlines (NWA), requests that either the proposed requirement for terminating action for Group 2 airplanes be removed from the NPRM or the compliance time for doing the termination action be extended from four years to six years. The ATA notes that there are no service instructions for the terminating action for Group 2 airplanes. The ATA also states that extending the compliance time will allow the development of the service instructions and an assessment of the requirement’s impact. NWA adds that it has not experienced extensive cracking that would warrant serious consideration or justification to mandate the terminating action (replacement of the NWW side and top panels). NWA also states that it would be very difficult to accomplish the replacement without a service bulletin. We agree with the commenter’s concern regarding lack of availability of service instructions for Group 2 airplanes; however, we do not consider that removing the terminating action or delaying this action until after the E:\FR\FM\06NOR1.SGM 06NOR1

Agencies

[Federal Register Volume 71, Number 214 (Monday, November 6, 2006)]
[Rules and Regulations]
[Pages 64881-64884]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-18471]



========================================================================
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. 71, No. 214 / Monday, November 6, 2006 / 
Rules and Regulations

[[Page 64881]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22812; Directorate Identifier 2005-NM-134-AD; 
Amendment 39-14811; AD 2006-22-14]
RIN 2120-AA64


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

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A330 airplanes and Model A340-200 and -300 series 
airplanes. This AD requires repetitive detailed inspections for 
cracking in the aft web of support rib 6 between certain bottom skin 
stringers on both wings; high frequency eddy current inspections for 
cracking of the attachment holes of the fuel pipes, and repair if 
necessary. This AD also provides for an optional modification, which 
extends a certain inspection threshold, and mandates, for certain 
airplanes, a new modification of support rib 6 on both wings, which 
ends the repetitive inspection requirement. This AD results from a 
report of significant cracking found in the aft web of support rib 6 on 
both wings. We are issuing this AD to prevent cracking in the aft web 
of support rib 6, which could result in overloading of adjacent ribs 
and the surrounding wing structure and consequent reduced structural 
integrity of the wing.

DATES: This AD becomes effective December 11, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 11, 
2006.

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

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the 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 street address stated in the 
ADDRESSES section.

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that would apply to certain 
Airbus Model A330 airplanes and Model A340-200 and -300 series 
airplanes. That supplemental NPRM was published in the Federal Register 
on May 26, 2006 (71 FR 30340). That supplemental NPRM proposed to 
require repetitive detailed inspections for cracking in the aft web of 
support rib 6 between certain bottom skin stringers on both wings; high 
frequency eddy current inspections for cracking of the attachment holes 
of the fuel pipes, and repair if necessary. The supplemental NPRM also 
provided for an optional modification, which would extend a certain 
inspection threshold. For certain airplanes, the supplemental NPRM 
proposed to require a new modification of support rib 6 on both wings, 
which would end the repetitive inspection requirement. The supplemental 
NPRM also proposed to reduce the applicability in the original NPRM.

Comment

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Request for Credit for Terminating Modification

    The Air Transport Association (ATA), on behalf of its member 
Northwest Airlines (NWA), asks that we recognize Airbus Modification 
54432 as terminating action for the repetitive inspection requirements 
in the supplemental NPRM. NWA states that this modification is being 
incorporated by Airbus in production as the ``production solution'' for 
the fatigue cracking problems. NWA adds that the modification will be 
installed on its Model A330 airplanes delivered with manufacturer's 
serial number 0778 and subsequent.
    We agree that Airbus Modification 54432 will be terminating action 
for the referenced repetitive inspections. However, that modification 
is not yet approved by either the European Aviation Safety Agency 
(EASA), which is the airworthiness authority for the European Union, or 
the FAA. The modification is currently in the approval process with the 
EASA. This modification is the production solution that installs a re-
designed rib for production airplanes with a new wing build. Once the 
modification is approved, the referenced EASA airworthiness directive 
will be revised to include this terminating action. After the 
modification is approved and available, operators may request an 
alternative method of compliance for installing the modification. We 
have not changed the AD in this regard.

Explanation of Change to the Supplemental NPRM

    Airbus Service Bulletins A300-57-3085 and A340-57-4093, both 
Revision 02, both dated September 29, 2005, were included in the 
service information section of the supplemental NPRM as the sources of 
service information for accomplishing the inspections. However, 
Revision 02 was inadvertently omitted from paragraph (l) of the 
supplemental NPRM; we have added Revision 02 to paragraph (l) 
accordingly.

[[Page 64882]]

Conclusion

    We have carefully reviewed the available data, including the 
comment 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.

Costs of Compliance

    This AD affects about 25 airplanes of U.S. registry.
    The inspections take about 4 work hours per airplane, at an average 
labor rate of $80 per work hour. Based on these figures, the estimated 
cost of the inspections for U.S. operators is $8,000, or $320 per 
airplane, per inspection cycle.
    The modification of support rib 6 on the left-hand wing takes about 
38 work hours per airplane, at an average labor rate of $80 per work 
hour. Required parts cost about $5,020 per airplane. Based on these 
figures, the estimated cost of this modification of the left-hand wing 
on U.S. operators is $201,500, or $8,060 per airplane.
    The modification of support rib 6 on the right-hand wing takes 
about 38 work hours per airplane, at an average labor rate of $80 per 
work hour. Required parts cost about $5,020 per airplane. Based on 
these figures, the estimated cost of this modification of the right-
hand wing on U.S. operators is $201,500, or $8,060 per airplane.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

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 
adding the following new airworthiness directive (AD):

2006-22-14 Airbus: Amendment 39-14811. Docket No. FAA-2005-22812; 
Directorate Identifier 2005-NM-134-AD.

Effective Date

    (a) This AD becomes effective December 11, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330 airplanes and Model 
A340-200 and -300 series airplanes, certificated in any category; on 
which Airbus Modification 41114 or 44599 was done during production; 
except those airplanes on which Airbus Modification 53883 was done 
during production.

Unsafe Condition

    (d) This AD results from a report of significant cracking found 
in the aft web of support rib 6 on both wings. We are issuing this 
AD to prevent cracking in the aft web of support rib 6, which could 
result in overloading of adjacent ribs and the surrounding wing 
structure and consequent reduced structural integrity of the wing.

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.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Repetitive Inspections

    (f) For Model A330 series airplanes on which Airbus Modification 
53882 was not done during production: At the applicable time 
specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, perform 
a detailed inspection for cracking in the aft web of support rib 6 
between bottom skin stringers 18 and 20 on both wings, and high 
frequency eddy current inspections for cracking of the attachment 
holes of the fuel pipe and fuel pipe mounting, by doing all the 
actions in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-57-3085, Revision 02, dated September 29, 
2005. If no crack is found during the initial inspections, repeat 
the inspections thereafter at intervals not to exceed 8,000 flight 
cycles or 25,000 flight hours, whichever is first, until the 
terminating action specified in paragraph (n) of this AD is done. If 
any crack is found during any inspection, repair as specified in 
paragraph (k) of this AD, or before further flight do the 
terminating action specified in paragraph (n) of this AD.
    (1) For airplanes that have accumulated 7,999 or fewer total 
flight cycles, and 24,999 or fewer total flight hours, as of the 
effective date of this AD: Do the inspections at the later of the 
times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
    (i) Before the accumulation of 8,000 total flight cycles or 
25,000 total flight hours, whichever is first.
    (ii) Within 8 months after the effective date of this AD.
    (2) For airplanes that have accumulated 8,000 or more total 
flight cycles, but fewer than 10,000 total flight cycles; or 25,000 
or more total flight hours, but fewer than 30,000 total flight 
hours; as of the effective date of this AD: Do the inspections at 
the later of the times specified in paragraphs (f)(2)(i) and 
(f)(2)(ii) of this AD.
    (i) Before the accumulation of 10,000 total flight cycles or 
30,000 total flight hours, whichever is first.
    (ii) Within 8 months after the effective date of this AD.
    (3) For airplanes that have accumulated 10,000 or more total 
flight cycles or 30,000 or more total flight hours as of the 
effective

[[Page 64883]]

date of this AD: Do the inspections within 3 months after the 
effective date of this AD.
    (g) For Model A330 series airplanes on which Airbus Modification 
53882 was done during production or on which Airbus Service Bulletin 
A330-57-3087, dated February 15, 2005, or Revision 01, dated 
September 22, 2005, has been done: Perform the applicable 
inspections required by paragraph (f) of this AD at the earliest of 
the initial inspection thresholds specified in Figure 4, Sheet 1, 
``Inspection Flow Chart'' of Airbus Service Bulletin A330-57-3085, 
Revision 02, dated September 29, 2005; or within 6 months after the 
effective date of this AD, whichever is later. Repeat the 
inspections required by paragraph (f) of this AD at the time 
specified in paragraph (f) of this AD, until the terminating action 
specified in paragraph (n) of this AD is done.
    (h) For Model A340 series airplanes on which Airbus Modification 
53882 was not done during production: Perform the inspections 
required by paragraph (f) of this AD at the applicable time 
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Perform 
the inspections by doing all the actions in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-57-4093, 
Revision 02, dated September 29, 2005. Repeat the inspections 
thereafter at intervals not to exceed 8,000 flight cycles or 30,200 
flight hours, whichever is first, until the terminating action 
specified in paragraph (n) of this AD is done.
    (1) For airplanes that have accumulated 7,999 or fewer total 
flight cycles, and 30,199 or fewer total flight hours, as of the 
effective date of this AD: Do the inspections at the later of the 
times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
    (i) Before the accumulation of 8,000 total flight cycles or 
30,200 total flight hours, whichever is first.
    (ii) Within 8 months after the effective date of this AD.
    (2) For airplanes that have accumulated 8,000 or more total 
flight cycles, but fewer than 10,000 total flight cycles; or 30,200 
or more total flight cycles, but fewer than 43,700 total flight 
hours, as of the effective date of this AD: Do the inspections at 
the later of the times specified in paragraphs (h)(2)(i) and 
(h)(2)(ii) of this AD.
    (i) Before the accumulation of 10,000 total flight cycles or 
43,700 total flight hours, whichever is first.
    (ii) Within 8 months after the effective date of this AD.
    (3) For airplanes that have accumulated 10,000 or more total 
flight cycles or 43,700 or more total flight hours as of the 
effective date of this AD: Do the inspections within 3 months after 
the effective date of this AD.
    (i) For Model A340 series airplanes on which Airbus Modification 
53882 was done during production or on which Airbus Service Bulletin 
A340-57-4095, dated February 15, 2005, or Revision 01, dated 
September 22, 2005, has been done: Perform the applicable 
inspections required by paragraph (f) of this AD at the earliest of 
the initial inspection thresholds specified in Figure 4, Sheet 1, 
``Inspection Flow Chart'' of Airbus Service Bulletin A340-57-4093, 
Revision 02, dated September 29, 2005; or within 6 months after the 
effective date of this AD, whichever is later. Repeat the 
inspections required by paragraph (f) of this AD at the time 
specified in paragraph (h) of this AD, until the terminating action 
specified in paragraph (n) of this AD is done.

Inspections Accomplished According to Previous Issue of Service 
Bulletins

    (j) Inspections accomplished before the effective date of this 
AD according to Airbus All Operator Telex A330-57A3085 or A340-
57A4093, each dated December 15, 2004; or Airbus Service Bulletin 
A330-57-3085 or A340-57-4093, each Revision 01, each dated March 25, 
2005; are considered acceptable for compliance with the 
corresponding inspections specified in this AD.

Repair

    (k) If any cracking is found during any inspection required by 
this AD: Before further flight, either repair and get a schedule for 
subsequent inspections, according to a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or 
its delegated agent); or accomplish the terminating action specified 
in paragraph (n) of this AD.

Optional Modification

    (l) Accomplishing the modification of the fuel pipe connector 
and the fastener holes of support rib 6 on both wings by doing all 
the actions specified in the Accomplishment Instructions of Airbus 
Service Bulletin A330-57-3087 or A340-57-4095, each dated February 
15, 2005, or Revision 01, each dated September 22, 2005, as 
applicable, extends the interval for the next inspection to the 
applicable post-modification inspection threshold specified in 
Figure 4, Sheet 1, ``Inspection Flow Chart'' of Airbus Service 
Bulletins A330-57-3085 or A340-57-4093, each Revision 02, each dated 
September 29, 2005, as applicable. After accomplishing that 
inspection, repeat the applicable inspections required by paragraph 
(f) or (h) of this AD at the applicable repetitive inspection 
interval specified in Figure 4 of the Accomplishment Instructions of 
the applicable service bulletin, until the terminating action 
specified in paragraph (n) of this AD is done.

Hard or Overweight Landing

    (m) For Model A330 series airplanes with 8,000 or more total 
flight cycles or 25,000 or more total flight hours, and Model A340 
series airplanes with 8,000 or more total flight cycles or 30,200 or 
more total flight hours that have not been modified in accordance 
with paragraph (n) of this AD: Before further flight after any hard 
or overweight landing of the airplane, accomplish the applicable 
follow-on inspections and any applicable corrective actions 
according to a method approved by either the Manager, International 
Branch, ANM-116; or the EASA (or its delegated agent). Accomplishing 
the inspections in Chapter 05-51-11, titled ``Inspection After Hard/
Overweight Landing--Inspection/Check,'' dated April 1, 2005, or July 
1, 2006, of the Airbus A330 Aircraft Maintenance Manual (AMM); or 
Chapter 05-51-11, titled ``Inspection After Hard/Overweight 
Landing--Inspection/Check,'' dated July 1, 2006, of the Airbus A340 
AMM; as applicable; and Airbus A330/A340 Technical Disposition (TD) 
TD/J1/S3/00608/2005, Issue C, dated April 26, 2005, titled 
``Inspections following hard landing, both wings,'' are approved 
methods. Operators can obtain the TD from Airbus.

Terminating Modification

    (n) For airplanes on which support rib 6 on both wings has not 
been repaired in accordance with paragraph (k) of this AD: Within 60 
months after the effective date of this AD, modify the fuel pipe 
connector and the fastener holes of support rib 6 on both wings by 
doing all the actions specified in the Accomplishment Instructions 
of Airbus Service Bulletin A330-57-3088 or A340-57-4096, each 
including Appendix 01, each dated September 21, 2005, as applicable. 
Accomplishing the modification in this paragraph ends the repetitive 
inspections required by this AD. Repair of support rib 6 on both 
wings before the effective date of this AD using Airbus A330/A340 
Repair Instruction R572-57023, Issue D, dated May 11, 2005; or R572-
57026, Issue C, dated December 2005; as applicable, ends the 
repetitive inspections required by this AD.

Alternative Methods of Compliance (AMOCs)

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

Related Information

    (p) French airworthiness directives F-2006-008 and F-2006-009, 
both dated January 4, 2006, also address the subject of this AD.

Material Incorporated by Reference

    (q) You must use the applicable Airbus service bulletins 
specified in Table 1 of this AD to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

[[Page 64884]]



                                  Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
        Airbus Service Bulletin                    Revision level                            Date
----------------------------------------------------------------------------------------------------------------
A330-57-3085..........................  02.................................  September 29, 2005.
A330-57-3087..........................  Original...........................  February 15, 2005.
A330-57-3087..........................  01.................................  September 22, 2005.
A330-57-3088, including Appendix 01...  Original...........................  September 21, 2005.
A340-57-4093..........................  02.................................  September 29, 2005.
A340-57-4095..........................  Original...........................  February 15, 2005.
A340-57-4095..........................  01.................................  September 22, 2005.
A340-57-4096, including Appendix 01...  Original...........................  September 21, 2005.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington, on October 25, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-18471 Filed 11-3-06; 8:45 am]
BILLING CODE 4910-13-P