Airworthiness Directives; Airbus Model A340-200 and A340-300 Series Airplanes, 70035-70038 [05-22789]

Download as PDF Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations email_subscription/ and allows FSIS customers to sign up for subscription options across eight categories. Options range from recalls to export information to regulations, directives and notices. Customers can add or delete subscriptions themselves and have the option to password protect their account. List of Subjects in 9 CFR Part 327 Imported Products. For the reasons set out in the preamble, FSIS is amending 9 CFR part 327 as follows: I PART 327—IMPORTED PRODUCTS 1. The authority citation for part 327 continues to read as follows: I 2005 (70 FR 55513) is effective November 14, 2005. FOR FURTHER INFORMATION CONTACT: Robert E. Donnelly, Senior Accountant, Office of Policy and Analysis, Farm Credit Administration, McLean, VA 22102–5090, (703) 883–4498, TTY (703) 883–4434; or Rebecca S. Orlich, Senior Attorney, Office of General Counsel, Farm Credit Administration, McLean, VA 22102–5090, (703) 883–4020, TTY (703) 883–4020. (12 U.S.C. 2252(a)(9) and (10)) Dated: November 15, 2005. Jeanette C. Brinkley, Secretary, Farm Credit Administration Board. [FR Doc. 05–23001 Filed 11–18–05; 8:45 am] BILLING CODE 6705–01–P Authority: 21 U.S.C. 601–695; 7 CFR 2.18, 2.53. § 327.2 DEPARTMENT OF TRANSPORTATION [Amended] 2. Section 327.2 is amended by adding Chile in alphabetical order to the list of countries in paragraph (b). Federal Aviation Administration Done at Washington, DC, on: October, 11, 2005. Barbara J. Masters, Administrator. [FR Doc. 05–22980 Filed 11–18–05; 8:45 am] [Docket No. FAA–2005–23005; Directorate Identifier 2003–NM–110–AD; Amendment 39–14379; AD 2005–23–21] BILLING CODE 3410–DM–P Airworthiness Directives; Airbus Model A340–200 and A340–300 Series Airplanes I FARM CREDIT ADMINISTRATION 14 CFR Part 39 RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: 12 CFR Part 627 RIN 3052–AC26 Title IV Conservators, Receivers, and Voluntary Liquidations; Receivership Repudiation Authorities; Effective Date Farm Credit Administration. ACTION: Notice of effective date. AGENCY: SUMMARY: The Farm Credit Administration (FCA) published a final rule under part 627 on September 22, 2005 (70 FR 55513). This final rule gives certainty to Farm Credit System institutions regarding how the Farm Credit System Insurance Corporation will treat qualifying participations and securitizations if the institution is subsequently placed in conservatorship or receivership. In accordance with 12 U.S.C. 2252, the effective date of the final rule is 30 days from the date of publication in the Federal Register during which either or both Houses of Congress are in session. Based on the records of the sessions of Congress, the effective date of the regulations is November 14, 2005. DATES: The regulation amending 12 CFR part 627, published on September 22, VerDate Aug<31>2005 16:13 Nov 18, 2005 Jkt 208001 SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A340–200 and A340–300 series airplanes. This AD requires repetitive inspections for cracking of the junction between the thrust reverser forward frame and the 12 o’clock and 6 o’clock beams; the thrust reverser common fittings; and the thrust reverser J-ring structure at the 12 o’clock and 6 o’clock positions; and related investigative and corrective actions. This AD results from fatigue and damage tolerance testing of the engine thrust reversers which revealed fatigue cracking of the junction between the thrust reverser forward frame and the 12 o’clock beam, and of the thrust reverser J-ring structure. We are issuing this AD to detect and correct such fatigue cracking, which could result in rupture of the J-ring, forward frame, or common fittings; loss of the thrust reverser system; or inadvertent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 70035 This AD becomes effective December 6, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 6, 2005. We must receive comments on this AD by January 20, 2006. 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; or Rohr Inc., 850 Lagoon Drive, Chula Vista, California 91912; for 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 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: 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 all Airbus Model A340–200 and A340–300 series airplanes. The DGAC advises that fatigue and damage tolerance testing of the engine thrust reversers revealed cracking of the junction between the thrust reverser forward frame and the 12 o’clock beam. The cracking of the junction was found after the accumulation of approximately 20,000 total flight cycles. In addition to the fatigue cracking that was found during fatigue tests, fatigue cracking of the J-ring was also found on in-service airplanes that had accumulated fewer than 6,666 total flight cycles. These conditions, if not corrected, could result in rupture of the J-ring, forward frame, or common fittings; loss of the thrust reverser system; or inadvertent deployment of a thrust reverser in flight E:\FR\FM\21NOR1.SGM 21NOR1 70036 Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations and consequent reduced controllability of the airplane. Relevant Service Information Airbus has issued Service Bulletin A340–78–4028, including Appendix 01, Revision 01, dated October 23, 2003. The service bulletin describes procedures for repetitive inspections for cracking of the junction between the thrust reverser forward frame and the 12 o’clock and 6 o’clock beams and the thrust reverser common fittings, and related investigative and corrective actions. The Airbus Service Bulletin refers to Rohr Service Bulletin RA34078–71, Revision 1, dated February 7, 2003, as an appropriate source of service information for accomplishing the eddy current inspections for cracking. The related investigative and corrective actions include performing eddy current inspections for missing fasteners, installing missing fasteners, replacing the thrust reverser with a new thrust Revision level Service bulletin CFM International CFM56–5C Alert Service Bulletin 78–A0072. CFM International CFM56–5C Alert Service Bulletin 78–A0073. Service Bulletin 78–A0072 describes procedures for repetitive eddy current inspections for cracking of the J-ring structure at the 12 o’clock and 6 o’clock positions, and corrective action if necessary. The corrective action procedures specify replacing the thrust reverser with a new thrust reverser. Service Bulletin 78–A0073 describes procedures for modifying the J-ring and replacing the 12 o’clock fitting (including inspecting machined parts for cracks and contacting the manufacturer if necessary.) 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 fatigue cracking of the J-ring and on the junction between the forward frame and the 12 o’clock beam, which could result in rupture of the Jring, forward frame, or common fittings, inadvertent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane. This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences VerDate Aug<31>2005 16:13 Nov 18, 2005 Jkt 208001 Date Including 2 January 27, 2004 ........... 1 January 27, 2004 ........... Rohr Alert Service Bulletin sion 2, dated January 27, Rohr Alert Service Bulletin sion 1, dated January 27, Among This AD, Service Bulletins, and French Airworthiness Directives.’’ Differences Among This AD, Service Bulletins, and French Airworthiness Directives French airworthiness directive 2003– 108(B) specifies certain compliance thresholds for the inspection of the thrust reversers since new. For certain airplanes, this AD would require you to perform the inspections at those thresholds or within 6 months after the effective date of the AD, whichever is latest. We have included a 6-month grace period to ensure that any airplane that is close to or has passed the threshold is not grounded as of the effective date of the AD. If any cracking is found on machined parts during the inspections specified in CFM International CFM56–5C Alert Service Bulletin 78–A0073, and the service bulletin specifies contacting Airbus or CFM for repair, this AD requires repairing those conditions using a method that we approve. If damage is found on any common fitting during the inspections specified in Airbus Service Bulletin A340–78– 4028, and the service bulletin specifies contacting Airbus for repair, this AD requires repairing those conditions using a method that we approve. Although Airbus Service Bulletin A340–78–4028 and CFM International CFM56–5C Alert Service Bulletin 78– A0072, specify reporting the replacement of any thrust reverser to Airbus or CFM, this AD does not include that requirement. Clarification of Inspection Terminology The French airworthiness directives specify a ‘‘visual inspection’’ and an ‘‘inspection’’ for cracking of the J-ring PO 00000 Frm 00006 reverser if any cracking is found or missing fasteners cannot be replaced, and contacting the manufacturer to report any damage. The DGAC mandated the Airbus service information and issued French airworthiness directives 2003–108(B), dated March 19, 2003; and F–2004–020, dated February 4, 2004, to ensure the continued airworthiness of these airplanes in France. The parts manufacturer has also issued the following service bulletins: Fmt 4700 Sfmt 4700 RA340A78–72, Revi2004 RA340A78–73, Revi2004 structure at the junction between the forward frame and the 12 o’clock and 6 o’clock beams of the engine thrust reversers. We refer to these inspections as ‘‘detailed inspections.’’ We have included the definition for a detailed inspection in a note in the AD. (This terminology is consistent with the terminology used in the service information.) Clarification of Optional Replacement If a crack is detected at the 12 o’clock fitting, the French airworthiness directive F–2004–020 includes replacing the thrust reverser as one option for the corrective action. 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. If an affected airplane is imported and placed on the U.S. Register in the future, the required actions would take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD would be $130 per airplane, per inspection cycle. 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, E:\FR\FM\21NOR1.SGM 21NOR1 Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations and this AD may be made effective in less than 30 days after it is published in the Federal Register. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the ADDRESSES section. Include ‘‘Docket No. FAA–2005–23005; Directorate Identifier 2003–NM–110–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. We will post all comments we receive, without change, to 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 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. 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 VerDate Aug<31>2005 16:13 Nov 18, 2005 Jkt 208001 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 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 2005–23–21 Airbus: Amendment 39–14379. Docket No. FAA–2005–23005; Directorate Identifier 2003–NM–110–AD. Effective Date (a) This AD becomes effective December 6, 2005. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 70037 Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A340–211, –212, and –213 and A340–311, –312, and –313 airplanes, certificated in any category. Unsafe Condition (d) This AD results from fatigue and damage tolerance testing of the engine thrust reversers which revealed fatigue cracking of the junction between the thrust reverser forward frame and the 12 o’clock beam, and of the thrust reverser J-ring structure. We are issuing this AD to detect and correct such fatigue cracking, which could result in rupture of the J-ring, forward frame, or common fittings; loss of the thrust reverser system; or inadvertent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane. 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/Investigative and Corrective Actions (f) Accomplish detailed and eddy current inspections for cracking of the junction between the thrust reverser forward frame and the 12 o’clock and 6 o’clock beams, and the thrust reverser common fittings, and related investigative and corrective actions, by doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–78–4028, Revision 01, dated October 23, 2003. Except, if damage is found on the common fittings, repair the damage using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. Do the inspections at the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD. Do any related investigative and corrective actions before further flight in accordance with the service bulletin. Repeat the inspections thereafter at intervals not to exceed 4,500 flight cycles on the thrust reverser. (1) For thrust reversers that have accumulated fewer than 4,500 total flight cycles since new as of the effective date of this AD: Before the accumulation of 4,500 total flight cycles on the thrust reverser since new, or within 2,166 flight cycles after the effective date of this AD, whichever is later. (2) For thrust reversers that have accumulated 4,500 or more total flight cycles since new as of the effective date of this AD: Before the accumulation of 6,666 total flight E:\FR\FM\21NOR1.SGM 21NOR1 70038 Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations cycles on the thrust reverser since new or within 6 months after the effective date of this AD, whichever is later. Note 2: Airbus Service Bulletin A340–78– 4028, Revision 01, dated October 23, 2003, references Rohr Service Bulletin RA34078– 71, Revision 1, dated February 7, 2003, as an additional source of service information for accomplishing the applicable actions in paragraph (f) of this AD. (g) At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Accomplish an eddy current inspection for cracking of the J-ring structure at the 12 o’clock and 6 o’clock positions by doing all the applicable actions in accordance with CFM International CFM56–5C Alert Service Bulletin 78–A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78–72, Revision 2, dated January 27, 2004. If no cracking is found: Repeat the inspection thereafter at intervals not to exceed 800 flight hours or 175 flight cycles on the thrust reverser, whichever is first. (1) Before the accumulation of 3,000 total flight cycles on any thrust reverser since new. (2) Within 800 flight hours or 175 flight cycles after the effective date of this AD, whichever is first. (h) If any cracking is found at the 12 o’clock position, before further flight, do the actions required by either paragraph (h)(1) or (h)(2) of this AD. (1) Replace the thrust reverser by doing all the applicable actions in accordance with CFM International CFM56–5C Alert Service Bulletin 78–A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78–72, Revision 2, dated January 27, 2004. (2) Modify the J-ring and replace the 12 o’clock fitting by doing all the applicable actions in accordance with CFM International CFM56–5C Alert Service Bulletin 78–A0073, Revision 1, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78–73, Revision 1, dated January 27, 2004. Except, if any cracking is found on machined parts, repair the damage using a method approved by the Manager, International Branch, ANM–116. Repeat the inspection of the 6 o’clock position only at the time specified in paragraph (g) of this AD. (i) If cracking is found at the 6 o’clock position: Before further flight, replace the thrust reverser by doing all the applicable actions in accordance with CFM International CFM56–5C Alert Service Bulletin 78–A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78–72, Revision 2, dated January 27, 2004. No Reporting Required (j) Although Airbus Service Bulletin A340– 78–4028, Revision 01, dated October 23, 2003; and CFM International CFM56–5C Alert Service Bulletin 78–A0072, Revision 2, dated January 27, 2004, specify reporting the replacement of any thrust reverser to Airbus or CFM, this AD does not include that requirement. VerDate Aug<31>2005 16:13 Nov 18, 2005 Jkt 208001 Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (k)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Federal Aviation Administration (l) French airworthiness directives 2003– 108(B), dated March 19, 2003; and F–2004– 020, dated February 4, 2004, also address the subject of this AD. Material Incorporated by Reference (m) You must use Airbus Service Bulletin A340–78–4028, Revision 01, excluding Appendix 01, dated October 23, 2003; CFM International CFM56–5C Alert Service Bulletin 78–A0072, Revision 2, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78–72, Revision 2, dated January 27, 2004; and CFM International CFM56–5C Alert Service Bulletin 78–A0073, Revision 1, dated January 27, 2004, including Rohr Alert Service Bulletin RA340A78–73, Revision 1, dated January 27, 2004; as applicable; 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; or Rohr Inc., 850 Lagoon Drive, Chula Vista, California 91912, 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. Issued in Renton, Washington, on November 9, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–22789 Filed 11–18–05; 8:45 am] BILLING CODE 4910–13–P Frm 00008 Fmt 4700 [Docket No. FAA–2005–23006; Directorate Identifier 2002–NM–51–AD; Amendment 39– 14380; AD 2005–23–22] RIN 2120–AA64 Airworthiness Directives; British Aerospace Model HS 748 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: Related Information PO 00000 14 CFR Part 39 Sfmt 4700 SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all British Aerospace Model HS 748 airplanes. This AD requires repetitive inspections for fatigue cracking, corrosion, and other related discrepancies of the rear pressure bulkhead and associated areas, and the fin attachment fittings, particularly the fin link beam; and related investigative and corrective actions. This AD results from a structural integrity audit of the airplane that showed the importance of inspecting for fatigue cracking and corrosion of these areas. We are issuing this AD to detect and correct cracking, corrosion, and other related discrepancies of the rear pressure bulkhead and associated areas, and the fin attachment fittings, particularly the fin link beam, which could result in damage to the airplane structure or injury to airplane occupants. DATES: This AD becomes effective December 6, 2005. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 6, 2005. We must receive comments on this AD by January 20, 2006. 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, E:\FR\FM\21NOR1.SGM 21NOR1

Agencies

[Federal Register Volume 70, Number 223 (Monday, November 21, 2005)]
[Rules and Regulations]
[Pages 70035-70038]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22789]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23005; Directorate Identifier 2003-NM-110-AD;
Amendment 39-14379; AD 2005-23-21]
RIN 2120-AA64

Airworthiness Directives; Airbus 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 all
Airbus Model A340-200 and A340-300 series airplanes. This AD requires
repetitive inspections for cracking of the junction between the thrust
reverser forward frame and the 12 o'clock and 6 o'clock beams; the
thrust reverser common fittings; and the thrust reverser J-ring
structure at the 12 o'clock and 6 o'clock positions; and related
investigative and corrective actions. This AD results from fatigue and
damage tolerance testing of the engine thrust reversers which revealed
fatigue cracking of the junction between the thrust reverser forward
frame and the 12 o'clock beam, and of the thrust reverser J-ring
structure. We are issuing this AD to detect and correct such fatigue
cracking, which could result in rupture of the J-ring, forward frame,
or common fittings; loss of the thrust reverser system; or inadvertent
deployment of a thrust reverser in flight and consequent reduced
controllability of the airplane.

DATES: This AD becomes effective December 6, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 6,
2005.
We must receive comments on this AD by January 20, 2006.

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; or Rohr Inc., 850 Lagoon Drive, Chula Vista, California 91912;
for 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 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on all Airbus Model A340-200 and A340-300
series airplanes. The DGAC advises that fatigue and damage tolerance
testing of the engine thrust reversers revealed cracking of the
junction between the thrust reverser forward frame and the 12 o'clock
beam. The cracking of the junction was found after the accumulation of
approximately 20,000 total flight cycles. In addition to the fatigue
cracking that was found during fatigue tests, fatigue cracking of the
J-ring was also found on in-service airplanes that had accumulated
fewer than 6,666 total flight cycles. These conditions, if not
corrected, could result in rupture of the J-ring, forward frame, or
common fittings; loss of the thrust reverser system; or inadvertent
deployment of a thrust reverser in flight

[[Page 70036]]

and consequent reduced controllability of the airplane.

Relevant Service Information

Airbus has issued Service Bulletin A340-78-4028, including Appendix
01, Revision 01, dated October 23, 2003. The service bulletin describes
procedures for repetitive inspections for cracking of the junction
between the thrust reverser forward frame and the 12 o'clock and 6
o'clock beams and the thrust reverser common fittings, and related
investigative and corrective actions.
The Airbus Service Bulletin refers to Rohr Service Bulletin
RA34078-71, Revision 1, dated February 7, 2003, as an appropriate
source of service information for accomplishing the eddy current
inspections for cracking. The related investigative and corrective
actions include performing eddy current inspections for missing
fasteners, installing missing fasteners, replacing the thrust reverser
with a new thrust reverser if any cracking is found or missing
fasteners cannot be replaced, and contacting the manufacturer to report
any damage.
The DGAC mandated the Airbus service information and issued French
airworthiness directives 2003-108(B), dated March 19, 2003; and F-2004-
020, dated February 4, 2004, to ensure the continued airworthiness of
these airplanes in France.
The parts manufacturer has also issued the following service
bulletins:

----------------------------------------------------------------------------------------------------------------
Revision
Service bulletin level Date Including
----------------------------------------------------------------------------------------------------------------
CFM International CFM56-5C Alert 2 January 27, 2004...... Rohr Alert Service Bulletin RA340A78-
Service Bulletin 78-A0072. 72, Revision 2, dated January 27,
2004
CFM International CFM56-5C Alert 1 January 27, 2004...... Rohr Alert Service Bulletin RA340A78-
Service Bulletin 78-A0073. 73, Revision 1, dated January 27,
2004
----------------------------------------------------------------------------------------------------------------

Service Bulletin 78-A0072 describes procedures for repetitive eddy
current inspections for cracking of the J-ring structure at the 12
o'clock and 6 o'clock positions, and corrective action if necessary.
The corrective action procedures specify replacing the thrust reverser
with a new thrust reverser. Service Bulletin 78-A0073 describes
procedures for modifying the J-ring and replacing the 12 o'clock
fitting (including inspecting machined parts for cracks and contacting
the manufacturer if necessary.)

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 fatigue
cracking of the J-ring and on the junction between the forward frame
and the 12 o'clock beam, which could result in rupture of the J-ring,
forward frame, or common fittings, inadvertent deployment of a thrust
reverser in flight and consequent reduced controllability of the
airplane. This AD requires accomplishing the actions specified in the
service information described previously, except as discussed under
``Differences Among This AD, Service Bulletins, and French
Airworthiness Directives.''

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

French airworthiness directive 2003-108(B) specifies certain
compliance thresholds for the inspection of the thrust reversers since
new. For certain airplanes, this AD would require you to perform the
inspections at those thresholds or within 6 months after the effective
date of the AD, whichever is latest. We have included a 6-month grace
period to ensure that any airplane that is close to or has passed the
threshold is not grounded as of the effective date of the AD.
If any cracking is found on machined parts during the inspections
specified in CFM International CFM56-5C Alert Service Bulletin 78-
A0073, and the service bulletin specifies contacting Airbus or CFM for
repair, this AD requires repairing those conditions using a method that
we approve.
If damage is found on any common fitting during the inspections
specified in Airbus Service Bulletin A340-78-4028, and the service
bulletin specifies contacting Airbus for repair, this AD requires
repairing those conditions using a method that we approve.
Although Airbus Service Bulletin A340-78-4028 and CFM International
CFM56-5C Alert Service Bulletin 78-A0072, specify reporting the
replacement of any thrust reverser to Airbus or CFM, this AD does not
include that requirement.

Clarification of Inspection Terminology

The French airworthiness directives specify a ``visual inspection''
and an ``inspection'' for cracking of the J-ring structure at the
junction between the forward frame and the 12 o'clock and 6 o'clock
beams of the engine thrust reversers. We refer to these inspections as
``detailed inspections.'' We have included the definition for a
detailed inspection in a note in the AD. (This terminology is
consistent with the terminology used in the service information.)

Clarification of Optional Replacement

If a crack is detected at the 12 o'clock fitting, the French
airworthiness directive F-2004-020 includes replacing the thrust
reverser as one option for the corrective action.

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.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required actions would take about 2 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the AD would be $130 per airplane, per
inspection cycle.

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,

[[Page 70037]]

and this AD may be made effective in less than 30 days after it is
published in the Federal Register.

Comments Invited

This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
23005; Directorate Identifier 2003-NM-110-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to 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 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.

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):

2005-23-21 Airbus: Amendment 39-14379. Docket No. FAA-2005-23005;
Directorate Identifier 2003-NM-110-AD.

Effective Date

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

Affected ADs

(b) None.

Applicability

(c) This AD applies to all Airbus Model A340-211, -212, and -213
and A340-311, -312, and -313 airplanes, certificated in any
category.

Unsafe Condition

(d) This AD results from fatigue and damage tolerance testing of
the engine thrust reversers which revealed fatigue cracking of the
junction between the thrust reverser forward frame and the 12
o'clock beam, and of the thrust reverser J-ring structure. We are
issuing this AD to detect and correct such fatigue cracking, which
could result in rupture of the J-ring, forward frame, or common
fittings; loss of the thrust reverser system; or inadvertent
deployment of a thrust reverser in flight and consequent reduced
controllability of the airplane.

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/Investigative and Corrective Actions

(f) Accomplish detailed and eddy current inspections for
cracking of the junction between the thrust reverser forward frame
and the 12 o'clock and 6 o'clock beams, and the thrust reverser
common fittings, and related investigative and corrective actions,
by doing all the actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340-78-4028, Revision 01,
dated October 23, 2003. Except, if damage is found on the common
fittings, repair the damage using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA.
Do the inspections at the later of the times specified in paragraphs
(f)(1) and (f)(2) of this AD. Do any related investigative and
corrective actions before further flight in accordance with the
service bulletin. Repeat the inspections thereafter at intervals not
to exceed 4,500 flight cycles on the thrust reverser.
(1) For thrust reversers that have accumulated fewer than 4,500
total flight cycles since new as of the effective date of this AD:
Before the accumulation of 4,500 total flight cycles on the thrust
reverser since new, or within 2,166 flight cycles after the
effective date of this AD, whichever is later.
(2) For thrust reversers that have accumulated 4,500 or more
total flight cycles since new as of the effective date of this AD:
Before the accumulation of 6,666 total flight

[[Page 70038]]

cycles on the thrust reverser since new or within 6 months after the
effective date of this AD, whichever is later.

Note 2: Airbus Service Bulletin A340-78-4028, Revision 01, dated
October 23, 2003, references Rohr Service Bulletin RA34078-71,
Revision 1, dated February 7, 2003, as an additional source of
service information for accomplishing the applicable actions in
paragraph (f) of this AD.

(g) At the later of the times specified in paragraphs (g)(1) and
(g)(2) of this AD: Accomplish an eddy current inspection for
cracking of the J-ring structure at the 12 o'clock and 6 o'clock
positions by doing all the applicable actions in accordance with CFM
International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2,
dated January 27, 2004, including Rohr Alert Service Bulletin
RA340A78-72, Revision 2, dated January 27, 2004. If no cracking is
found: Repeat the inspection thereafter at intervals not to exceed
800 flight hours or 175 flight cycles on the thrust reverser,
whichever is first.
(1) Before the accumulation of 3,000 total flight cycles on any
thrust reverser since new.
(2) Within 800 flight hours or 175 flight cycles after the
effective date of this AD, whichever is first.
(h) If any cracking is found at the 12 o'clock position, before
further flight, do the actions required by either paragraph (h)(1)
or (h)(2) of this AD.
(1) Replace the thrust reverser by doing all the applicable
actions in accordance with CFM International CFM56-5C Alert Service
Bulletin 78-A0072, Revision 2, dated January 27, 2004, including
Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January
27, 2004.
(2) Modify the J-ring and replace the 12 o'clock fitting by
doing all the applicable actions in accordance with CFM
International CFM56-5C Alert Service Bulletin 78-A0073, Revision 1,
dated January 27, 2004, including Rohr Alert Service Bulletin
RA340A78-73, Revision 1, dated January 27, 2004. Except, if any
cracking is found on machined parts, repair the damage using a
method approved by the Manager, International Branch, ANM-116.
Repeat the inspection of the 6 o'clock position only at the time
specified in paragraph (g) of this AD.
(i) If cracking is found at the 6 o'clock position: Before
further flight, replace the thrust reverser by doing all the
applicable actions in accordance with CFM International CFM56-5C
Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004,
including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated
January 27, 2004.

No Reporting Required

(j) Although Airbus Service Bulletin A340-78-4028, Revision 01,
dated October 23, 2003; and CFM International CFM56-5C Alert Service
Bulletin 78-A0072, Revision 2, dated January 27, 2004, specify
reporting the replacement of any thrust reverser to Airbus or CFM,
this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

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

Related Information

(l) French airworthiness directives 2003-108(B), dated March 19,
2003; and F-2004-020, dated February 4, 2004, also address the
subject of this AD.

Material Incorporated by Reference

(m) You must use Airbus Service Bulletin A340-78-4028, Revision
01, excluding Appendix 01, dated October 23, 2003; CFM International
CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January
27, 2004, including Rohr Alert Service Bulletin RA340A78-72,
Revision 2, dated January 27, 2004; and CFM International CFM56-5C
Alert Service Bulletin 78-A0073, Revision 1, dated January 27, 2004,
including Rohr Alert Service Bulletin RA340A78-73, Revision 1, dated
January 27, 2004; as applicable; 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; or Rohr Inc., 850 Lagoon Drive, Chula Vista,
California 91912, 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.

Issued in Renton, Washington, on November 9, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22789 Filed 11-18-05; 8:45 am]
BILLING CODE 4910-13-P

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