Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, and -342 Airplanes; and Model A340-200 and A340-300 Series Airplanes, 55236-55239 [05-18522]

Download as PDF 55236 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations Effective Date Issued in Renton, Washington, on September 9, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–18521 Filed 9–20–05; 8:45 am] (a) This AD becomes effective October 6, 2005. Affected ADs (b) None. Applicability BILLING CODE 4910–13–P (c) This AD applies to all BAE Systems (Operations) Limited Model HS 748 series 2A and series 2B airplanes, certificated in any category. DEPARTMENT OF TRANSPORTATION Unsafe Condition (d) This AD results from a report that pintle pins could be installed in an incorrect manner during maintenance without maintenance personnel being aware (or having feedback) that the pin was installed incorrectly. The FAA is issuing this AD to prevent jamming or collapse of the nose landing gear (NLG), which could result in damage to the airplane structure or injury to passengers or crew. 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. Modifying the Undercarriage of the Nose Landing Gear (f) Within 64 months after the effective date of this AD, modify the undercarriage of the NLG in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin HS748–32–104, dated April 9, 2002. Alternative Methods of Compliance (AMOCs) (g) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (h) British airworthiness directive 003–04– 2002 also addresses the subject of this AD. Material Incorporated by Reference (i) You must use BAE Systems (Operations) Limited Service Bulletin HS748–32–104, dated April 9, 2002, 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 this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171, 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 https:// 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 https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. VerDate Aug<31>2005 14:27 Sep 20, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22452; Directorate Identifier 2001–NM–336–AD; Amendment 39–14277; AD 2005–19–12] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–301, –321, –322, –341, and –342 Airplanes; and Model A340–200 and A340–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330–301, –321, –322, –341, and –342 airplanes; and Model A340–200 and A340–300 series airplanes. This AD requires repetitive inspections for cracks of the inboard lower flange and radius of the left- and right-hand outboard floor beams at frame (FR) 48, and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports that cracks were found during fatigue tests at the attachment between the canted lower flange of the floor beam and the pressure diaphragm in front of FR48 on both left- and righthand floor beams; and that an additional crack was found in the flange radius of the floor beam. We are issuing this AD to detect and correct such cracking, which could propagate and result in reduced structural integrity of the fuselage. Effective October 6, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 6, 2005. We must receive comments on this AD by November 21, 2005. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to https:// dms.dot.gov and follow the instructions DATES: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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. You may examine the contents of the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL–401, Washington, DC. This docket number is FAA–2005– 22452; the directorate identifier for this docket is 2001–NM–336–AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, ANM– 116, International Branch, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited Although this is a final rule that was not preceded by notice and an opportunity for public comment, we invite you to submit any relevant written data, views, or arguments regarding this AD. Include ‘‘Docket No. FAA–2005–22452; Directorate Identifier 2001–NM–336–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to https:// 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 E:\FR\FM\21SER1.SGM 21SER1 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://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. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A330– 301, –321, –322, –341, and –342 airplanes; and Model A340–200 and A340–300 series airplanes. The DGAC advises that cracks were found during fatigue tests at the attachment between the canted lower flange of the floor beam and the pressure diaphragm in front of frame (FR) 48 on both left- and right-hand floor beams. The cracks extended between two fasteners close to FR48 on the canted lower flange of the floor beam. In addition, another crack was found in the flange radius of the floor beam. Further investigation revealed that the cracks resulted from excessive bending of the canted lower flange of the floor beam. Fatigue cracks could propagate from one fastener to another. This condition, if not corrected, could result in reduced structural integrity of the fuselage. Relevant Service Information Airbus has issued Service Bulletin A330–53–3014, Revision 05, dated June 20, 2003 (for Model A330–301, –321, –322, –341, and –342 airplanes); and Service Bulletin A340–53–4022, Revision 05, dated June 16, 2003 (for Model A340–200 and A340–300 series airplanes). The service bulletins describe procedures for doing repetitive high-frequency eddy current (HFEC) inspections for cracks of the inboard lower flange and radius of the left- and right-hand outboard floor beams at FR48. The service bulletins also describe procedures for reporting inspection findings to Airbus. If no cracks are found during an HFEC inspection, the service bulletins specify that operators repeat the inspection. If any crack is found during any HFEC VerDate Aug<31>2005 14:27 Sep 20, 2005 Jkt 205001 inspection, the service bulletins give procedures for related investigative and corrective actions as follows: • For cracks at the radius, the service bulletins specify that operators should contact Airbus for repair instructions before further flight. • For cracks at the flange, the service bulletins specify that operators should measure the total length of the crack. If the crack is within certain limits, the service bulletins give procedures for stop-drilling the crack before further flight, and for repairing the crack within 500 flight cycles after the stop-drilling by installing stainless steel doublers under the floor beams. If the crack is outside certain limits, the service bulletins specify that operators should contact Airbus for repair instructions before further flight. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directives 2001–506(B), dated October 17, 2001, and 2001– 507(B), dated October 17, 2001, to ensure the continued airworthiness of these airplanes in France. Airbus has also issued Service Bulletins A330–53–3013, Revision 03 dated December 23, 1999 (for Model A330–301, –321, –322, –341, and –342 airplanes); and Service Bulletin A340– 53–4021, Revision 05, dated January 27, 2003 (for Model A340–200 and A340– 300 series airplanes). These service bulletins provide an optional terminating action for the repetitive inspections of the inboard lower flange. The terminating action is installing new stainless steel doublers under the floor beam to limit the bending movement of the canted lower flange. The installation involves removing certain fasteners and doing a rotating probe inspection for cracks of the fastener holes. If any crack is found, the service bulletins specify contacting Airbus for repair instructions. 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. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 55237 type design that are certificated for operation in the United States. Therefore, we are issuing this AD to detect and correct cracks between the canted lower flange of the floor beam and the pressure diaphragm in front of FR48 on both left- and right-hand floor beams; and cracks in the flange radius of the floor beam; which could propagate and result in reduced structural integrity of the fuselage. This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Among the AD, the French Airworthiness Directives, and the Service Bulletins.’’ Operators should note that, in consonance with the findings of the DGAC, this proposed AD allows operators to continue the repetitive inspections instead of doing the terminating action. Additionally, in certain cases, operators that detect cracking may defer the repair for a specified period of time. In making these determinations, we consider that, in the case of this AD, long-term continued operational safety is adequately assured by doing the repetitive inspections to detect cracking before it represents a hazard to the airplane, and by doing repairs within the specified time limits. Differences Among the AD, the French Airworthiness Directives, and the Service Bulletins The applicability of the French airworthiness directives excludes airplanes on which Airbus Service Bulletin A330–53–3013 or A340–53– 4021 was accomplished in service. However, we have not excluded those airplanes in the applicability of this AD; rather, this AD includes a requirement to accomplish the actions specified in those service bulletins. This requirement will ensure that the actions specified in the applicable service bulletin and required by this AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this AD unless an alternative method of compliance is approved. This difference has been coordinated with the DGAC. The French airworthiness directives specify a compliance time based on the time ‘‘since new.’’ However, this AD specifies a compliance time after the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. This decision is based on our determination that ‘‘since new’’ may be interpreted differently by different operators. We E:\FR\FM\21SER1.SGM 21SER1 55238 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations find that our proposed terminology is generally understood within the industry and records will always exist that establish these dates with certainty. The service bulletins specify that you may contact the manufacturer for instructions on how to repair certain conditions, but this AD would require you to repair those conditions using a method that we or the DGAC (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this AD, a repair we, or the DGAC, approve would be acceptable for compliance with this AD. Although the Accomplishment Instructions of Airbus Service Bulletins Costs of Compliance A330–53–3014, Revision 05, and A340– 53–4022, Revision 05, provide procedures for reporting certain information to the manufacturer, this AD would not require those actions. Clarification of Optional Terminating Action The service bulletins describe procedures for installing a stainless steel doubler, which is an optional terminating action for the repetitive inspections of both the inboard lower flange and the radius. The manufacturer has determined that the crack in the radius is a direct consequence of the load re-distribution following cracking of the fastener holes. The stainless steel doubler reinforces the area of the fastener holes. 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. The following table provides the estimated costs to comply with this AD for any affected airplane that might be imported and placed on the U.S. Register in the future. ESTIMATED COSTS Work hours Action HFEC inspection, per inspection cycle ........................... Optional terminating action ............................................. 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. 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 VerDate Aug<31>2005 14:27 Sep 20, 2005 Jkt 205001 Average labor rate per hour 2 18 $65 65 Parts cost None ................. $1,930 .............. 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 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 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Cost per airplane $130, per inspection cycle. $3,100. 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 2005–19–12 Airbus: Amendment 39–14277. Docket No. FAA–2005–22452; Directorate Identifier 2001–NM–336–AD. Effective Date (a) This AD becomes effective October 6, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330– 301, –321, –322, –341, and –342 airplanes; and Model A340–211, –212, –213, –311, –312, and –313 airplanes; certificated in any category; on which Airbus Modification 42418 has not been accomplished in production. Unsafe Condition (d) This AD results from reports that cracks were found during fatigue tests at the attachment between the canted lower flange of the floor beam and the pressure diaphragm in front of frame (FR) 48 on both left- and right-hand floor beams; and that an additional crack was found in the flange radius of the floor beam. The FAA is issuing this AD to detect and correct such cracking, E:\FR\FM\21SER1.SGM 21SER1 Federal Register / Vol. 70, No. 182 / Wednesday, September 21, 2005 / Rules and Regulations which could propagate and 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. Repetitive Inspections (f) At the applicable times in paragraph (f)(1) or (f)(2) of this AD: Do high-frequency eddy current inspection for cracks of the inboard lower flange and radius of the lefthand and right-hand outboard floor beams at FR48. Do all inspections in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 1 of this AD. Doing the action in paragraph (h) of this AD terminates the repetitive inspection requirements of this paragraph. (1) For Airbus Model A330–301, –321, –322, –341, and –342 airplanes: Do the first inspection before the accumulation of 8,400 flight cycles since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later; and repeat the 55239 inspection thereafter at intervals not to exceed 3,860 total flight cycles or 15,050 flight hours, whichever occurs earlier. (2) For Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes: Do the first inspection before the accumulation of the earlier of 9,200 flight cycles or 70,000 flight hours since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, or within 6 months after the effective date of this AD, whichever occurs later; and repeat the inspection thereafter at intervals not to exceed 3,070 flight cycles. TABLE 1.—SERVICE BULLETINS For airbus model— Airbus service bulletin— A330–301, –321, –322, –341, and –342 airplanes ........................................................... A340–211, –212, –213, –311, –312, and –313 airplanes ................................................. A330–53–3014, Revision 05, dated June 20, 2003. A340–53–4022, Revision 05, dated June 16, 2003. Related Investigative and Corrective Actions (g) If any crack is found during any inspection required by paragraph (f) of this AD: Do the applicable actions in paragraph (g)(1) and (g)(2) of this AD. (1) For cracks at the radius: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the Direction ´ ´ Geanearale de l’Aviation Civile (DGAC) (or its delegated agent). (2) For cracks at the flange: Before further flight, measure the total length of the crack and do the applicable action in paragraph (g)(2)(i) and (g)(2)(ii) of this AD. (i) If the crack is less than 12 mm (0.472 inch) in length: Before further flight, stopdrill the crack and, within 500 flight cycles after stop-drilling the crack, do the action in paragraph (h) of this AD. (ii) If the crack is greater than or equal to 12 mm (0.472 inch) in length: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM–116; or the ´ ´ Direction Geanearale de l’Aviation Civile (DGAC) (or its delegated agent). Optional Terminating Action (h) Installing a stainless steel doubler in accordance with Airbus Service Bulletin A330–53–3013, Revision 03, December 23, 1999; or Airbus Service Bulletin A340–53– 4021, Revision 05, dated January 27, 2003; as applicable; terminates the repetitive inspection requirements of paragraph (f) of this AD. If any crack is found during this installation while doing the rotating probe inspection of the fastener holes: Before further flight, repair the crack according to a method approved by either the Manager, International Branch, ANM–116; or the DGAC (or its delegated agent). No Reporting Required (i) Although the Accomplishment Instructions of the service bulletins identified in Table 1 of this AD describe procedures for reporting certain information to the manufacturer, this AD would not require those actions. VerDate Aug<31>2005 14:27 Sep 20, 2005 Jkt 205001 Alternative Methods of Compliance (AMOCs) (j) 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. Issued in Renton, Washington, on September 9, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–18522 Filed 9–20–05; 8:45 am] BILLING CODE 4910–13–P Related Information (k) French airworthiness directives 2001– 506(B) and 2001–507(B), both dated October 17, 2001, also address the subject of this AD. Material Incorporated by Reference (l) You must use the service information identified in Table 2 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 https:// 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 https://www.archives.gov/federalregister/cfr/ibr-locations.html. TABLE 2.—MATERIAL INCORPORATED BY REFERENCE Service Bulletin Revision level A330–53–3013 03 A330–53–3014 A340–53–4021 05 05 A340–53–4022 05 PO 00000 Frm 00015 Fmt 4700 Date December 23, 1999. June 20, 2003. January 27, 2003. June 16, 2003. Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20347; Directorate Identifier 2004–NM–226–AD; Amendment 39–14284; AD 2005–19–19] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–300, –400, –500, –600, –700, –700C, –800 and –900 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737–300, –400, –500, –600, –700, –700C, –800 and –900 series airplanes. This AD requires installing an updated version of the operational program software (OPS) and certain other software in the flight management computers (FMCs); and doing configuration checks to ensure that certain software is properly installed and doing other specified actions. This AD also requires reinstalling software, if necessary. This AD results from one operator reporting FMC map shifts on several Model 737–400 series airplanes with dual FMCs, using OPS version U10.4A. We are issuing this AD to prevent the FMC from displaying the E:\FR\FM\21SER1.SGM 21SER1

Agencies

[Federal Register Volume 70, Number 182 (Wednesday, September 21, 2005)]
[Rules and Regulations]
[Pages 55236-55239]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18522]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22452; Directorate Identifier 2001-NM-336-AD;
Amendment 39-14277; AD 2005-19-12]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Airplanes; and Model A340-200 and A340-300 Series
Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes;
and Model A340-200 and A340-300 series airplanes. This AD requires
repetitive inspections for cracks of the inboard lower flange and
radius of the left- and right-hand outboard floor beams at frame (FR)
48, and related investigative and corrective actions if necessary. This
AD also provides an optional terminating action for the repetitive
inspections. This AD results from reports that cracks were found during
fatigue tests at the attachment between the canted lower flange of the
floor beam and the pressure diaphragm in front of FR48 on both left-
and right-hand floor beams; and that an additional crack was found in
the flange radius of the floor beam. We are issuing this AD to detect
and correct such cracking, which could propagate and result in reduced
structural integrity of the fuselage.

DATES: Effective October 6, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 6,
2005.
We must receive comments on this AD by November 21, 2005.

ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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.
You may examine the contents of the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401,
Washington, DC. This docket number is FAA-2005-22452; the directorate
identifier for this docket is 2001-NM-336-AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, ANM-
116, International Branch, FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Although this is a final rule that was not preceded by notice and
an opportunity for public comment, we invite you to submit any relevant
written data, views, or arguments regarding this AD. Include ``Docket
No. FAA-2005-22452; Directorate Identifier 2001-NM-336-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
AD. We will consider all comments received by the closing date and may
amend the AD in light of those comments.
We will post all comments we receive, without change, to https://
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

[[Page 55237]]

Privacy Act Statement in the Federal Register published on April 11,
2000 (65 FR 19477-78), or you may visit https://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at https://
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.

Discussion

The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified us that an unsafe
condition may exist on certain Airbus Model A330-301, -321, -322, -341,
and -342 airplanes; and Model A340-200 and A340-300 series airplanes.
The DGAC advises that cracks were found during fatigue tests at the
attachment between the canted lower flange of the floor beam and the
pressure diaphragm in front of frame (FR) 48 on both left- and right-
hand floor beams. The cracks extended between two fasteners close to
FR48 on the canted lower flange of the floor beam. In addition, another
crack was found in the flange radius of the floor beam. Further
investigation revealed that the cracks resulted from excessive bending
of the canted lower flange of the floor beam. Fatigue cracks could
propagate from one fastener to another. This condition, if not
corrected, could result in reduced structural integrity of the
fuselage.

Relevant Service Information

Airbus has issued Service Bulletin A330-53-3014, Revision 05, dated
June 20, 2003 (for Model A330-301, -321, -322, -341, and -342
airplanes); and Service Bulletin A340-53-4022, Revision 05, dated June
16, 2003 (for Model A340-200 and A340-300 series airplanes). The
service bulletins describe procedures for doing repetitive high-
frequency eddy current (HFEC) inspections for cracks of the inboard
lower flange and radius of the left- and right-hand outboard floor
beams at FR48. The service bulletins also describe procedures for
reporting inspection findings to Airbus. If no cracks are found during
an HFEC inspection, the service bulletins specify that operators repeat
the inspection. If any crack is found during any HFEC inspection, the
service bulletins give procedures for related investigative and
corrective actions as follows:
For cracks at the radius, the service bulletins specify
that operators should contact Airbus for repair instructions before
further flight.
For cracks at the flange, the service bulletins specify
that operators should measure the total length of the crack. If the
crack is within certain limits, the service bulletins give procedures
for stop-drilling the crack before further flight, and for repairing
the crack within 500 flight cycles after the stop-drilling by
installing stainless steel doublers under the floor beams. If the crack
is outside certain limits, the service bulletins specify that operators
should contact Airbus for repair instructions before further flight.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directives
2001-506(B), dated October 17, 2001, and 2001-507(B), dated October 17,
2001, to ensure the continued airworthiness of these airplanes in
France.
Airbus has also issued Service Bulletins A330-53-3013, Revision 03
dated December 23, 1999 (for Model A330-301, -321, -322, -341, and -342
airplanes); and Service Bulletin A340-53-4021, Revision 05, dated
January 27, 2003 (for Model A340-200 and A340-300 series airplanes).
These service bulletins provide an optional terminating action for the
repetitive inspections of the inboard lower flange. The terminating
action is installing new stainless steel doublers under the floor beam
to limit the bending movement of the canted lower flange. The
installation involves removing certain fasteners and doing a rotating
probe inspection for cracks of the fastener holes. If any crack is
found, the service bulletins specify contacting Airbus for repair
instructions.

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. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC'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 detect and correct cracks
between the canted lower flange of the floor beam and the pressure
diaphragm in front of FR48 on both left- and right-hand floor beams;
and cracks in the flange radius of the floor beam; which could
propagate and result in reduced structural integrity of the fuselage.
This AD requires accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Among the AD, the French Airworthiness Directives, and
the Service Bulletins.''
Operators should note that, in consonance with the findings of the
DGAC, this proposed AD allows operators to continue the repetitive
inspections instead of doing the terminating action. Additionally, in
certain cases, operators that detect cracking may defer the repair for
a specified period of time. In making these determinations, we consider
that, in the case of this AD, long-term continued operational safety is
adequately assured by doing the repetitive inspections to detect
cracking before it represents a hazard to the airplane, and by doing
repairs within the specified time limits.

Differences Among the AD, the French Airworthiness Directives, and the
Service Bulletins

The applicability of the French airworthiness directives excludes
airplanes on which Airbus Service Bulletin A330-53-3013 or A340-53-4021
was accomplished in service. However, we have not excluded those
airplanes in the applicability of this AD; rather, this AD includes a
requirement to accomplish the actions specified in those service
bulletins. This requirement will ensure that the actions specified in
the applicable service bulletin and required by this AD are
accomplished on all affected airplanes. Operators must continue to
operate the airplane in the configuration required by this AD unless an
alternative method of compliance is approved. This difference has been
coordinated with the DGAC.
The French airworthiness directives specify a compliance time based
on the time ``since new.'' However, this AD specifies a compliance time
after the date of issuance of the original standard airworthiness
certificate or the date of issuance of the original export certificate
of airworthiness. This decision is based on our determination that
``since new'' may be interpreted differently by different operators. We

[[Page 55238]]

find that our proposed terminology is generally understood within the
industry and records will always exist that establish these dates with
certainty.
The service bulletins specify that you may contact the manufacturer
for instructions on how to repair certain conditions, but this AD would
require you to repair those conditions using a method that we or the
DGAC (or its delegated agent) approve. In light of the type of repair
that would be required to address the unsafe condition, and consistent
with existing bilateral airworthiness agreements, we have determined
that, for this AD, a repair we, or the DGAC, approve would be
acceptable for compliance with this AD.
Although the Accomplishment Instructions of Airbus Service
Bulletins A330-53-3014, Revision 05, and A340-53-4022, Revision 05,
provide procedures for reporting certain information to the
manufacturer, this AD would not require those actions.

Clarification of Optional Terminating Action

The service bulletins describe procedures for installing a
stainless steel doubler, which is an optional terminating action for
the repetitive inspections of both the inboard lower flange and the
radius. The manufacturer has determined that the crack in the radius is
a direct consequence of the load re-distribution following cracking of
the fastener holes. The stainless steel doubler reinforces the area of
the fastener holes.

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.
The following table provides the estimated costs to comply with
this AD for any affected airplane that might be imported and placed on
the U.S. Register in the future.

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average labor
Action Work hours rate per hour Parts cost Cost per airplane
--------------------------------------------------------------------------------------------------------------------------------------------------------
HFEC inspection, per inspection cycle. 2 $65 None.......................... $130, per inspection cycle.
Optional terminating action........... 18 65 $1,930........................ $3,100.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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.

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 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
adding the following new airworthiness directive (AD):

2005-19-12 Airbus: Amendment 39-14277. Docket No. FAA-2005-22452;
Directorate Identifier 2001-NM-336-AD.

Effective Date

(a) This AD becomes effective October 6, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A330-301, -321, -322, -341,
and -342 airplanes; and Model A340-211, -212, -213, -311, -312, and
-313 airplanes; certificated in any category; on which Airbus
Modification 42418 has not been accomplished in production.

Unsafe Condition

(d) This AD results from reports that cracks were found during
fatigue tests at the attachment between the canted lower flange of
the floor beam and the pressure diaphragm in front of frame (FR) 48
on both left- and right-hand floor beams; and that an additional
crack was found in the flange radius of the floor beam. The FAA is
issuing this AD to detect and correct such cracking,

[[Page 55239]]

which could propagate and 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.

Repetitive Inspections

(f) At the applicable times in paragraph (f)(1) or (f)(2) of
this AD: Do high-frequency eddy current inspection for cracks of the
inboard lower flange and radius of the left-hand and right-hand
outboard floor beams at FR48. Do all inspections in accordance with
the Accomplishment Instructions of the applicable service bulletin
in Table 1 of this AD. Doing the action in paragraph (h) of this AD
terminates the repetitive inspection requirements of this paragraph.
(1) For Airbus Model A330-301, -321, -322, -341, and -342
airplanes: Do the first inspection before the accumulation of 8,400
flight cycles since the date of issuance of the original standard
airworthiness certificate or the date of issuance of the original
export certificate of airworthiness, or within 6 months after the
effective date of this AD, whichever occurs later; and repeat the
inspection thereafter at intervals not to exceed 3,860 total flight
cycles or 15,050 flight hours, whichever occurs earlier.
(2) For Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes: Do the first inspection before the accumulation of the
earlier of 9,200 flight cycles or 70,000 flight hours since the date
of issuance of the original standard airworthiness certificate or
the date of issuance of the original export certificate of
airworthiness, or within 6 months after the effective date of this
AD, whichever occurs later; and repeat the inspection thereafter at
intervals not to exceed 3,070 flight cycles.

Table 1.--Service Bulletins
----------------------------------------------------------------------------------------------------------------
For airbus model-- Airbus service bulletin--
----------------------------------------------------------------------------------------------------------------
A330-301, -321, -322, -341, and -342 A330-53-3014, Revision 05, dated June 20, 2003.
airplanes.
A340-211, -212, -213, -311, -312, A340-53-4022, Revision 05, dated June 16, 2003.
and -313 airplanes.
----------------------------------------------------------------------------------------------------------------

Related Investigative and Corrective Actions

(g) If any crack is found during any inspection required by
paragraph (f) of this AD: Do the applicable actions in paragraph
(g)(1) and (g)(2) of this AD.
(1) For cracks at the radius: Before further flight, repair the
crack according to a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the Direction Ge[aacute]ne[aacute]rale de l'Aviation Civile
(DGAC) (or its delegated agent).
(2) For cracks at the flange: Before further flight, measure the
total length of the crack and do the applicable action in paragraph
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) If the crack is less than 12 mm (0.472 inch) in length:
Before further flight, stop-drill the crack and, within 500 flight
cycles after stop-drilling the crack, do the action in paragraph (h)
of this AD.
(ii) If the crack is greater than or equal to 12 mm (0.472 inch)
in length: Before further flight, repair the crack according to a
method approved by either the Manager, International Branch, ANM-
116; or the Direction Ge[aacute]ne[aacute]rale de l'Aviation Civile
(DGAC) (or its delegated agent).

Optional Terminating Action

(h) Installing a stainless steel doubler in accordance with
Airbus Service Bulletin A330-53-3013, Revision 03, December 23,
1999; or Airbus Service Bulletin A340-53-4021, Revision 05, dated
January 27, 2003; as applicable; terminates the repetitive
inspection requirements of paragraph (f) of this AD. If any crack is
found during this installation while doing the rotating probe
inspection of the fastener holes: Before further flight, repair the
crack according to a method approved by either the Manager,
International Branch, ANM-116; or the DGAC (or its delegated agent).

No Reporting Required

(i) Although the Accomplishment Instructions of the service
bulletins identified in Table 1 of this AD describe procedures for
reporting certain information to the manufacturer, this AD would not
require those actions.

Alternative Methods of Compliance (AMOCs)

(j) 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.

Related Information

(k) French airworthiness directives 2001-506(B) and 2001-507(B),
both dated October 17, 2001, also address the subject of this AD.

Material Incorporated by Reference

(l) You must use the service information identified in Table 2
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 https://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 https://
www.archives.gov/federal-register/cfr/ibr-locations.html.

Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Service Bulletin level Date
------------------------------------------------------------------------
A330-53-3013................... 03 December 23, 1999.
A330-53-3014................... 05 June 20, 2003.
A340-53-4021................... 05 January 27, 2003.
A340-53-4022................... 05 June 16, 2003.
------------------------------------------------------------------------

Issued in Renton, Washington, on September 9, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-18522 Filed 9-20-05; 8:45 am]
BILLING CODE 4910-13-P

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