Airworthiness Directives; Airbus Model A330 Airplanes, and Model A340-200 and A340-300 Series Airplanes, 53770-53773 [E8-21727]

Download as PDF 53770 Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 62CP/63CP), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–27A6062, dated July 6, 2007. (2) For airplanes on which the status of any spoiler actuator is unknown (unknown number of accumulated flight hours, unknown date of manufacture and/or unknown serial number) the actuator must be considered as having exceeded 55,750 total flight hours. (3) For airplanes on which all three hydraulic circuits have a spoiler actuator that has accumulated or exceeds 55,000 total flight hours: Before the accumulation of 55,750 total flight hours or within 700 flight hours after the effective date of this AD, whichever occurs later, on at least one hydraulic circuit, interchange the spoiler actuator with a serviceable unit from another hydraulic circuit, or replace the spoiler actuator with a serviceable unit, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 27–6060, dated February 18, 2008. (4) For airplanes on which the actions required by paragraph (f)(1) of this AD, and, as applicable, paragraph (f)(3) of this AD have been accomplished, each airplane must continue to have at least one hydraulic circuit fitted with spoiler actuators that do not exceed 55,750 total flight hours. Note 1: For the purposes of this AD, a serviceable unit is a unit that has accumulated less than 55,750 flight hours. (5) The operator must not interchange or replace spoiler actuators on more than two hydraulic circuits at the same time. This will mitigate the risk of having a malfunction on the three hydraulic systems at the same time. pwalker on PROD1PC71 with PROPOSALS Note 2: This AD differs from the MCAI and/or service information as follows: (1) This AD does not include the reporting requirement specified in paragraph (1) of the MCAI. The MCAI carried this requirement forward from European Aviation Safety Agency (EASA) Airworthiness Directive 2007–0245, dated September 5, 2007. We previously determined that no action was required on our part regarding EASA AD 2007–0245. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from 17:08 Sep 16, 2008 Jkt 214001 [Docket No. FAA–2008–0980; Directorate Identifier 2008–NM–008–AD] inspection to determine if certain fasteners are broken or cracked, and corrective actions if necessary. This proposed AD results from a report that incorrect torque values could damage the bracket. We are proposing this AD to prevent a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by October 17, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. RIN 2120–AA64 FAA AD Differences VerDate Aug<31>2005 a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Examining the AD Docket Related Information (h) Refer to MCAI EASA Airworthiness Directive 2008–0058, dated March 20, 2008; and Airbus Service Bulletins A300–27–6060, dated February 18, 2008; and A300– 27A6062, dated July 6, 2007; for related information. Issued in Renton, Washington, on September 9, 2008. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–21724 Filed 9–16–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Airbus Model A330 Airplanes, and Model A340–200 and A340–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A330, A340–200, and A340–300 series airplanes. The existing AD currently requires repetitive inspections of a certain bracket that attaches the flight deck instrument panel to the airplane structure; related investigative and corrective actions if necessary; and replacement of the existing bracket with a titaniumreinforced bracket, which ends the repetitive inspections in the existing AD. This proposed AD would add requirements only for airplanes on which the existing bracket was replaced with a titanium-reinforced bracket in accordance with the existing AD. The additional requirement is a one-time PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2008–0980; Directorate Identifier E:\FR\FM\17SEP1.SGM 17SEP1 Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 2008–NM–008–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On December 21, 2006, we issued AD 2006–26–12, amendment 39–14870 (72 FR 256, January 4, 2007), for certain Airbus Model A330, A340–200, and A340–300 series airplanes. That AD superseded AD 2005–06–08, amendment 39–14016 (70 FR 13345, March 21, 2005) and requires repetitive inspections of a certain bracket that attaches the flight deck instrument panel to the airplane structure; replacement of the bracket with a new, improved bracket; and related investigative and corrective actions if necessary. That AD further requires replacement of the existing bracket with a titanium-reinforced bracket, which would end the repetitive inspections. AD 2006–26–12 resulted from a report of cracking damage found on certain brackets that were replaced per the requirements of AD 2005–06–08. We issued AD 2006–26–12 to prevent a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, and consequent reduced controllability of the airplane. Actions Since Existing AD Was Issued Since we issued AD 2006–26–12, we have received a report that incorrect torque values could damage the bracket. These incorrect torque values were included in Airbus Service Bulletins A330–25–3249 and A340–25–4245, both dated May 3, 2005. We referred to those service bulletins in AD 2006–26–12 as the appropriate sources of service information for replacing the existing bracket with a titanium-reinforced bracket. Airbus has now revised these service bulletins (both Revision 01, both dated July 10, 2007) to include the correct torque values. The European Aviation Safety Agency (EASA) mandated the service information and issued EASA airworthiness directives 2007–0281 and 2007–0282, both dated November 6, 2007, to ensure the continued airworthiness of these airplanes in the European Union. Relevant Service Information As stated above, Airbus has issued Mandatory Service Bulletins A330–25– 3249 and A340–25–4245, both Revision 01, and both dated July 10, 2007. The procedures in Revision 01 of the service bulletins are essentially the same as the procedures in the original issue. However, Revision 01 of the service bulletins specifies new procedures for airplanes on which the bracket has been replaced in accordance with the procedures specified in the original issue. The new procedures are removing the fasteners of the titanium-reinforced bracket and, if a fastener is broken, doing a detailed inspection for cracking of the horizontal beam. If any crack is found, the service bulletins specify the corrective action of contacting Airbus for repair procedures. If no crack is found, the service bulletins specify the corrective action of installing new fasteners on the bracket. FAA’s Determination and Requirements of the Proposed AD These airplanes 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 53771 airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2006–26–12 and would retain the requirements of the existing AD. This proposed AD would also require accomplishing the actions specified in Airbus Mandatory Service Bulletins A330–25–3249 and A340–25–4245, both Revision 01, and both dated July 10, 2007, as discussed under ‘‘Difference Between the Proposed AD and the EASA Airworthiness Directives.’’ Difference Between the Proposed AD and the EASA Airworthiness Directives The EASA airworthiness directives specify contacting Airbus for instructions on how to repair certain conditions. This proposed AD requires repairing those conditions using a method that we or the EASA 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 proposed AD, a repair we or the EASA (or its delegated agent) approve would be acceptable for compliance with this proposed AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. This proposed AD would affect about 24 Model A330 series airplanes of U.S. registry. There are currently no affected Model A340–200 and –300 series airplanes of U.S. registry. However, if one of these airplanes is imported and put on the U.S. Register in the future, these cost estimates would also apply to those airplanes. ESTIMATED COSTS pwalker on PROD1PC71 with PROPOSALS Action Inspections (required by AD 2006–26–12). Replacement and investigative actions (required by AD 2006–26–12). One-time inspection (new proposed action). VerDate Aug<31>2005 17:08 Sep 16, 2008 Average labor rate per hour Work hours Parts Cost per airplane Fleet cost 1 $0 $80, per inspection cycle ...... $1,920, per inspection cycle. 9 80 330 $1,050 ................................... $25,200. 2 Jkt 214001 $80 80 0 $160 ...................................... Up to $3,840. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\17SEP1.SGM 17SEP1 53772 Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed 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 proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. pwalker on PROD1PC71 with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: VerDate Aug<31>2005 17:08 Sep 16, 2008 Jkt 214001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14870 (72 FR 256, January 4, 2007) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2008–0980; Directorate Identifier 2008–NM–008–AD. Comments Due Date (a) The FAA must receive comments on this AD action by October 17, 2008. Affected ADs (b) This AD supersedes AD 2006–26–12. Applicability (c) This AD applies to all Airbus Model A330 airplanes, and Model A340–200 and A340–300 series airplanes; certificated in any category; except those airplanes identified in paragraphs (c)(1), (c)(2) and (c)(3) of this AD. (1) Model A330 airplanes, and Model A340–200, and A340–300 series airplanes on which Airbus Modification 53446 has been incorporated in production. (2) Model A330 airplanes on which Airbus Service Bulletin A330–25–3249, Revision 01, dated July 10, 2007, has been embodied in service. (3) Model A340–200 and –300 series airplanes on which Airbus Service Bulletin A340–25–4245, Revision 01, dated July 10, 2007, has been embodied in service. Unsafe Condition (d) This AD results from a report that incorrect torque values could damage a certain bracket that attaches the flight deck instrument panel to the airplane structure. We are issuing this AD to prevent a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, 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. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the service bulletins identified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD, as applicable. (1) For the requirements of paragraphs (g), (h), and (i) of this AD: Airbus Service Bulletins A330–25–3227 and A340–25–4230, both Revision 01, both dated May 3, 2005. Accomplishment before February 8, 2007 (the effective date of AD 2006–26–12) of Airbus Service Bulletins A330–25–3227 and A340–25–4230, both including Appendix 01, both dated June 17, 2004, as applicable, is an acceptable means of compliance for paragraphs (g), (h), and (i) of this AD. (2) For the requirements of paragraph (k) of this AD done before the effective date of this AD: Airbus Service Bulletins A330–25–3249 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 and A340–25–4245, both dated May 3, 2005, as applicable. (3) For the requirements of paragraph (k) of this AD done after the effective date of this AD, and for the requirements of paragraph (l) of this AD: Airbus Mandatory Service Bulletins A330–25–3249 and A340–25–4245, both Revision 01, both dated July 10, 2007, as applicable. Restatement of the Requirements of AD 2006–26–12 Initial Inspection (g) At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, perform a detailed inspection of the bracket having part number (P/N) F2511012920000, which attaches the flight deck instrument panel to airplane structure, in accordance with the applicable service bulletin. (1) For Model A330 series airplanes: Prior to the accumulation of 16,500 total flight cycles, or within 60 days after April 25, 2005 (the effective date of AD 2005–06–08, amendment 39–14016, which was superseded by AD 2006–26–12), whichever is later. (2) For Model A340–200 and –300 series airplanes: Prior to the accumulation of 9,700 total flight cycles, or within 2,700 flight cycles after April 25, 2005, whichever is later. 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.’’ No Cracking/Repetitive Inspections (h) If no crack is found during the initial inspection required by paragraph (g) of this AD: Repeat the inspection thereafter at the applicable interval specified in paragraph (h)(1) or (h)(2) of this AD, until the replacement specified in paragraph (k) of this AD has been accomplished. (1) For Model A330 series airplanes: Intervals not to exceed 13,800 flight cycles. (2) For Model A340–200 and –300 series airplanes: Intervals not to exceed 7,000 flight cycles. Crack Found/Replacement and Repetitive Inspections (i) If any crack is found during any inspection required by paragraph (g) or (h) of this AD: Do the actions in paragraphs (i)(1) and (i)(2) of this AD, except as provided by paragraph (j) of this AD, until accomplishment of the replacement required by paragraph (k) of this AD. (1) Before further flight: Replace the cracked bracket with a new, improved bracket having P/N F2511012920095, in accordance with the service bulletin. (2) Repeat the inspection of the replaced bracket as required by paragraph (g) of this AD, at the time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. Then, do repetitive inspections or replace the bracket as E:\FR\FM\17SEP1.SGM 17SEP1 Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules specified in paragraph (h) or (i) of this AD, as applicable. (i) For Model A330 series airplanes: Within 16,500 flight cycles after replacing the bracket. (ii) For Model A340–200 and –300 series airplanes: Within 9,700 flight cycles after replacing the bracket. (j) If both flanges of a bracket are found broken during any inspection required by this AD: Before further flight, replace the bracket as specified in paragraph (i) of this AD and perform any applicable related investigative and corrective actions (which may include inspections for damage to surrounding structure caused by the broken bracket, and corrective actions for any damage that is found), in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Replacement of Brackets/Investigative and Corrective Actions (k) Except as required by paragraph (i)(1) of this AD: Within 72 months after February 8, 2007 (the effective date of AD 2006–26– 12), replace existing brackets having P/N F2511012920000 or P/N F2511012920095 with titanium-reinforced brackets having P/N F2511305220096; and perform any related investigative and corrective actions (which may include detailed inspections for cracking of the bracket or damage to surrounding structure caused by a broken bracket, and applicable corrective actions for any damage that is found); in accordance with the applicable service bulletin. If any crack is found, before further flight, repair in accordance with the applicable service bulletin. Replacement of the affected bracket with a titanium-reinforced bracket having P/ N F2511305220096 ends the repetitive inspections required by paragraph (h) or (i) of this AD. Although the service bulletins specify to submit certain information to the manufacturer, this AD does not include that requirement. total flight cycles, or within 20 months after the effective date of this AD, whichever occurs first. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) AMOCs approved previously in accordance with AD 2006–26–12 are approved as AMOCs for the corresponding provisions of this AD. Related Information (n) EASA airworthiness directives 2007– 0281 and 2007–0282, both dated November 6, 2007, also address the subject of this AD. Issued in Renton, Washington, on September 9, 2008. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–21727 Filed 9–16–08; 8:45 am] BILLING CODE 4910–13–P Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Rocco Viselli, Aerospace Engineer, Airframe and Propulsion Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7331; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 [Docket No. FAA–2008–0977; Directorate Identifier 2008–NM–124–AD] pwalker on PROD1PC71 with PROPOSALS One-Time Inspection (l) For airplanes on which the actions required by paragraph (k) of this AD have been accomplished before the effective date of this AD: At the applicable time in paragraph (l)(1) or (l)(2) of this AD, remove the fasteners of the titanium-reinforced bracket and, if a fastener is broken, do a detailed inspection for cracking of the horizontal beam. Do all applicable corrective actions before further flight. Do all actions in accordance with the applicable service bulletin. Where the applicable service bulletin specifies to contact Airbus, before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent). (1) For Model A330 series airplanes: Prior to the accumulation of 16,500 total flight cycles, or within 20 months after the effective date of this AD, whichever occurs first. (2) For Model A340–200 and –300 series airplanes: Prior to the accumulation of 12,400 Airworthiness Directives; Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Jkt 214001 * * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by October 17, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Federal Aviation Administration RIN 2120–AA64 17:08 Sep 16, 2008 The assessment showed that insufficient electrical bonding between the refuel/defuel shutoff valves and the aircraft structure could occur due to the presence of a nonconductive gasket (Gask-O-Seal). In addition, it was also determined that the presence of an anodic coating on the shutoff valve electrical conduit connection fitting could affect electrical bonding. The above conditions, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. DEPARTMENT OF TRANSPORTATION New Requirements of This AD VerDate Aug<31>2005 53773 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Bombardier Aerospace has completed a system safety review of the CL–600–2B19 aircraft fuel system against the new fuel tank safety standards * * *. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. E:\FR\FM\17SEP1.SGM 17SEP1

Agencies

[Federal Register Volume 73, Number 181 (Wednesday, September 17, 2008)]
[Proposed Rules]
[Pages 53770-53773]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-21727]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0980; Directorate Identifier 2008-NM-008-AD]
RIN 2120-AA64


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

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A330, A340-200, and 
A340-300 series airplanes. The existing AD currently requires 
repetitive inspections of a certain bracket that attaches the flight 
deck instrument panel to the airplane structure; related investigative 
and corrective actions if necessary; and replacement of the existing 
bracket with a titanium-reinforced bracket, which ends the repetitive 
inspections in the existing AD. This proposed AD would add requirements 
only for airplanes on which the existing bracket was replaced with a 
titanium-reinforced bracket in accordance with the existing AD. The 
additional requirement is a one-time inspection to determine if certain 
fasteners are broken or cracked, and corrective actions if necessary. 
This proposed AD results from a report that incorrect torque values 
could damage the bracket. We are proposing this AD to prevent a cracked 
bracket. Failure of this bracket, combined with failure of the 
horizontal beam, could result in collapse of the left part of the 
flight deck instrument panel, and consequent reduced controllability of 
the airplane.

DATES: We must receive comments on this proposed AD by October 17, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0980; 
Directorate Identifier

[[Page 53771]]

2008-NM-008-AD'' at the beginning of your comments. We specifically 
invite comments on the overall regulatory, economic, environmental, and 
energy aspects of this proposed AD. We will consider all comments 
received by the closing date and may amend this proposed AD because of 
those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 21, 2006, we issued AD 2006-26-12, amendment 39-14870 
(72 FR 256, January 4, 2007), for certain Airbus Model A330, A340-200, 
and A340-300 series airplanes. That AD superseded AD 2005-06-08, 
amendment 39-14016 (70 FR 13345, March 21, 2005) and requires 
repetitive inspections of a certain bracket that attaches the flight 
deck instrument panel to the airplane structure; replacement of the 
bracket with a new, improved bracket; and related investigative and 
corrective actions if necessary. That AD further requires replacement 
of the existing bracket with a titanium-reinforced bracket, which would 
end the repetitive inspections. AD 2006-26-12 resulted from a report of 
cracking damage found on certain brackets that were replaced per the 
requirements of AD 2005-06-08. We issued AD 2006-26-12 to prevent a 
cracked bracket. Failure of this bracket, combined with failure of the 
horizontal beam, could result in collapse of the left part of the 
flight deck instrument panel, and consequent reduced controllability of 
the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-26-12, we have received a report that 
incorrect torque values could damage the bracket. These incorrect 
torque values were included in Airbus Service Bulletins A330-25-3249 
and A340-25-4245, both dated May 3, 2005. We referred to those service 
bulletins in AD 2006-26-12 as the appropriate sources of service 
information for replacing the existing bracket with a titanium-
reinforced bracket. Airbus has now revised these service bulletins 
(both Revision 01, both dated July 10, 2007) to include the correct 
torque values.
    The European Aviation Safety Agency (EASA) mandated the service 
information and issued EASA airworthiness directives 2007-0281 and 
2007-0282, both dated November 6, 2007, to ensure the continued 
airworthiness of these airplanes in the European Union.

Relevant Service Information

    As stated above, Airbus has issued Mandatory Service Bulletins 
A330-25-3249 and A340-25-4245, both Revision 01, and both dated July 
10, 2007. The procedures in Revision 01 of the service bulletins are 
essentially the same as the procedures in the original issue. However, 
Revision 01 of the service bulletins specifies new procedures for 
airplanes on which the bracket has been replaced in accordance with the 
procedures specified in the original issue. The new procedures are 
removing the fasteners of the titanium-reinforced bracket and, if a 
fastener is broken, doing a detailed inspection for cracking of the 
horizontal beam. If any crack is found, the service bulletins specify 
the corrective action of contacting Airbus for repair procedures. If no 
crack is found, the service bulletins specify the corrective action of 
installing new fasteners on the bracket.

FAA's Determination and Requirements of the Proposed AD

    These airplanes 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 EASA has kept the FAA informed 
of the situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2006-26-12 and would retain the 
requirements of the existing AD. This proposed AD would also require 
accomplishing the actions specified in Airbus Mandatory Service 
Bulletins A330-25-3249 and A340-25-4245, both Revision 01, and both 
dated July 10, 2007, as discussed under ``Difference Between the 
Proposed AD and the EASA Airworthiness Directives.''

Difference Between the Proposed AD and the EASA Airworthiness 
Directives

    The EASA airworthiness directives specify contacting Airbus for 
instructions on how to repair certain conditions. This proposed AD 
requires repairing those conditions using a method that we or the EASA 
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 proposed 
AD, a repair we or the EASA (or its delegated agent) approve would be 
acceptable for compliance with this proposed AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. This proposed AD would affect about 24 
Model A330 series airplanes of U.S. registry. There are currently no 
affected Model A340-200 and -300 series airplanes of U.S. registry. 
However, if one of these airplanes is imported and put on the U.S. 
Register in the future, these cost estimates would also apply to those 
airplanes.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                Average labor                      Cost per
            Action               Work hours     rate per hour       Parts          airplane         Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD                 1             $80              $0  $80, per          $1,920, per
 2006-26-12).                                                                   inspection        inspection
                                                                                cycle.            cycle.
Replacement and investigative               9              80             330  $1,050..........  $25,200.
 actions (required by AD 2006-
 26-12).
One-time inspection (new                    2              80               0  $160............  Up to $3,840.
 proposed action).
----------------------------------------------------------------------------------------------------------------


[[Page 53772]]

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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 proposed 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14870 (72 FR 256, January 4, 2007) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2008-0980; Directorate Identifier 2008-NM-
008-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October 
17, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-26-12.

Applicability

    (c) This AD applies to all Airbus Model A330 airplanes, and 
Model A340-200 and A340-300 series airplanes; certificated in any 
category; except those airplanes identified in paragraphs (c)(1), 
(c)(2) and (c)(3) of this AD.
    (1) Model A330 airplanes, and Model A340-200, and A340-300 
series airplanes on which Airbus Modification 53446 has been 
incorporated in production.
    (2) Model A330 airplanes on which Airbus Service Bulletin A330-
25-3249, Revision 01, dated July 10, 2007, has been embodied in 
service.
    (3) Model A340-200 and -300 series airplanes on which Airbus 
Service Bulletin A340-25-4245, Revision 01, dated July 10, 2007, has 
been embodied in service.

Unsafe Condition

    (d) This AD results from a report that incorrect torque values 
could damage a certain bracket that attaches the flight deck 
instrument panel to the airplane structure. We are issuing this AD 
to prevent a cracked bracket. Failure of this bracket, combined with 
failure of the horizontal beam, could result in collapse of the left 
part of the flight deck instrument panel, 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.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the service bulletins identified in 
paragraphs (f)(1), (f)(2), and (f)(3) of this AD, as applicable.
    (1) For the requirements of paragraphs (g), (h), and (i) of this 
AD: Airbus Service Bulletins A330-25-3227 and A340-25-4230, both 
Revision 01, both dated May 3, 2005. Accomplishment before February 
8, 2007 (the effective date of AD 2006-26-12) of Airbus Service 
Bulletins A330-25-3227 and A340-25-4230, both including Appendix 01, 
both dated June 17, 2004, as applicable, is an acceptable means of 
compliance for paragraphs (g), (h), and (i) of this AD.
    (2) For the requirements of paragraph (k) of this AD done before 
the effective date of this AD: Airbus Service Bulletins A330-25-3249 
and A340-25-4245, both dated May 3, 2005, as applicable.
    (3) For the requirements of paragraph (k) of this AD done after 
the effective date of this AD, and for the requirements of paragraph 
(l) of this AD: Airbus Mandatory Service Bulletins A330-25-3249 and 
A340-25-4245, both Revision 01, both dated July 10, 2007, as 
applicable.

Restatement of the Requirements of AD 2006-26-12

Initial Inspection

    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD, perform a detailed inspection of the bracket 
having part number (P/N) F2511012920000, which attaches the flight 
deck instrument panel to airplane structure, in accordance with the 
applicable service bulletin.
    (1) For Model A330 series airplanes: Prior to the accumulation 
of 16,500 total flight cycles, or within 60 days after April 25, 
2005 (the effective date of AD 2005-06-08, amendment 39-14016, which 
was superseded by AD 2006-26-12), whichever is later.
    (2) For Model A340-200 and -300 series airplanes: Prior to the 
accumulation of 9,700 total flight cycles, or within 2,700 flight 
cycles after April 25, 2005, whichever is later.

    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.''

No Cracking/Repetitive Inspections

    (h) If no crack is found during the initial inspection required 
by paragraph (g) of this AD: Repeat the inspection thereafter at the 
applicable interval specified in paragraph (h)(1) or (h)(2) of this 
AD, until the replacement specified in paragraph (k) of this AD has 
been accomplished.
    (1) For Model A330 series airplanes: Intervals not to exceed 
13,800 flight cycles.
    (2) For Model A340-200 and -300 series airplanes: Intervals not 
to exceed 7,000 flight cycles.

Crack Found/Replacement and Repetitive Inspections

    (i) If any crack is found during any inspection required by 
paragraph (g) or (h) of this AD: Do the actions in paragraphs (i)(1) 
and (i)(2) of this AD, except as provided by paragraph (j) of this 
AD, until accomplishment of the replacement required by paragraph 
(k) of this AD.
    (1) Before further flight: Replace the cracked bracket with a 
new, improved bracket having P/N F2511012920095, in accordance with 
the service bulletin.
    (2) Repeat the inspection of the replaced bracket as required by 
paragraph (g) of this AD, at the time specified in paragraph 
(i)(2)(i) or (i)(2)(ii) of this AD. Then, do repetitive inspections 
or replace the bracket as

[[Page 53773]]

specified in paragraph (h) or (i) of this AD, as applicable.
    (i) For Model A330 series airplanes: Within 16,500 flight cycles 
after replacing the bracket.
    (ii) For Model A340-200 and -300 series airplanes: Within 9,700 
flight cycles after replacing the bracket.
    (j) If both flanges of a bracket are found broken during any 
inspection required by this AD: Before further flight, replace the 
bracket as specified in paragraph (i) of this AD and perform any 
applicable related investigative and corrective actions (which may 
include inspections for damage to surrounding structure caused by 
the broken bracket, and corrective actions for any damage that is 
found), in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent).

Replacement of Brackets/Investigative and Corrective Actions

    (k) Except as required by paragraph (i)(1) of this AD: Within 72 
months after February 8, 2007 (the effective date of AD 2006-26-12), 
replace existing brackets having P/N F2511012920000 or P/N 
F2511012920095 with titanium-reinforced brackets having P/N 
F2511305220096; and perform any related investigative and corrective 
actions (which may include detailed inspections for cracking of the 
bracket or damage to surrounding structure caused by a broken 
bracket, and applicable corrective actions for any damage that is 
found); in accordance with the applicable service bulletin. If any 
crack is found, before further flight, repair in accordance with the 
applicable service bulletin. Replacement of the affected bracket 
with a titanium-reinforced bracket having P/N F2511305220096 ends 
the repetitive inspections required by paragraph (h) or (i) of this 
AD. Although the service bulletins specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

New Requirements of This AD

One-Time Inspection

    (l) For airplanes on which the actions required by paragraph (k) 
of this AD have been accomplished before the effective date of this 
AD: At the applicable time in paragraph (l)(1) or (l)(2) of this AD, 
remove the fasteners of the titanium-reinforced bracket and, if a 
fastener is broken, do a detailed inspection for cracking of the 
horizontal beam. Do all applicable corrective actions before further 
flight. Do all actions in accordance with the applicable service 
bulletin. Where the applicable service bulletin specifies to contact 
Airbus, before further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA (or its delegated agent).
    (1) For Model A330 series airplanes: Prior to the accumulation 
of 16,500 total flight cycles, or within 20 months after the 
effective date of this AD, whichever occurs first.
    (2) For Model A340-200 and -300 series airplanes: Prior to the 
accumulation of 12,400 total flight cycles, or within 20 months 
after the effective date of this AD, whichever occurs first.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (2) AMOCs approved previously in accordance with AD 2006-26-12 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (n) EASA airworthiness directives 2007-0281 and 2007-0282, both 
dated November 6, 2007, also address the subject of this AD.

    Issued in Renton, Washington, on September 9, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-21727 Filed 9-16-08; 8:45 am]
BILLING CODE 4910-13-P
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