Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes Equipped With International Aero Engines (IAE) Model V2500-A1 Engines or Model V25xx-A5 Series Engines, 75316-75319 [E8-29182]

Download as PDF 75316 Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations 0095 (for Model 757–200, –200PF, and –200CB series airplanes) or 757–28–0096 (for Model 757–300 series airplanes), both Revision 1, both dated June 4, 2008; as applicable. The other specified actions must be done before further flight after changing the fuel boost pump wiring. Actions accomplished before the effective date of this AD in accordance with Boeing Special Attention Service Bulletin 757–28–0095 or 757–28–0096, both dated June 18, 2007, are considered acceptable for compliance with the corresponding actions in this paragraph. (g)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Philip Sheridan, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6441; fax (425) 917–6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. jlentini on PROD1PC65 with RULES Material Incorporated by Reference (h) You must use Boeing Special Attention Service Bulletin 757–28–0095, Revision 1, dated June 4, 2008; or Boeing Special Attention Service Bulletin 757–28–0096, Revision 1, dated June 4, 2008; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1, fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. (3) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. 16:21 Dec 10, 2008 Jkt 217001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Alternative Methods of Compliance (AMOCs) VerDate Aug<31>2005 Issued in Renton, Washington, on November 28, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–29079 Filed 12–10–08; 8:45 am] [Docket No. FAA–2008–1274; Directorate Identifier 2008–NM–197–AD; Amendment 39–15764; AD 2008–25–06] RIN 2120–AA64 Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes Equipped With International Aero Engines (IAE) Model V2500–A1 Engines or Model V25xx–A5 Series Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: * * * Airbus has advised that an incorrect part number has been introduced in the IPC (illustrated parts catalog) * * * for the rear engine mount barrel nut. This problem affects Airbus A319, A320 and A321 models with IAE (International Aero Engine) V2500– A5 engines. The part number introduced in error is not certificated for the IAE V2500–A5 engine installation and, if installed, may fail in service. * * * * * Failure of the rear engine mount barrel nut could result in reduced structural integrity of the rear engine mount and possible separation of the engine from the airplane, and a consequent hazard to the airplane and persons and property on the ground. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective December 26, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 26, 2008. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 We must receive comments on this AD by January 12, 2009. 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. 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 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: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Emergency Airworthiness Directive 2008–0191–E, dated October 20, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: DGAC–France AD 90–079–009(B) R1 [and corresponding FAA AD 90–22–08, amendment 39–6781 (corrected on November 8, 1990, 55 FR 47028)] introduced an inspection and daily rectification action on Airbus A320–231 aircraft in order to prevent failure of one or more of the engine rear mount barrel nuts. Subsequent to the above problem, Airbus has advised that an incorrect part number has been introduced in the IPC (illustrated parts catalog) (reference 71–22–11 Figure 80B item 180) for the rear engine mount barrel nut. This problem affects Airbus A319, A320 and A321 models with IAE (International Aero Engine) V2500–A5 engines. E:\FR\FM\11DER1.SGM 11DER1 Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations The part number introduced in error is not certificated for the IAE V2500–A5 engine installation and, if installed, may fail in service. This Airworthiness Directive (AD), which supersedes DGAC–France AD 90–079–009(B) R1, mandates the inspections required to determine the standard of barrel nut installed and the corrective actions, as necessary, for the aircraft with V2500–A1 or –A5 engines installed. Failure of the rear engine mount barrel nut could result in reduced structural integrity of the rear engine mount and possible separation of the engine from the airplane, and a consequent hazard to the airplane and persons and property on the ground. Required actions include inspecting for broken barrel nuts. The corrective actions include replacing the barrel nut with a different barrel nut and replacing the associated bolts, washers, and retainers; and contacting Airbus for corrective action if any affected barrel nut is found broken and doing that corrective action. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued All Operator Telex A320–71A1045, dated October 17, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. jlentini on PROD1PC65 with RULES FAA’s Determination and Requirements of this AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between the AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. VerDate Aug<31>2005 16:21 Dec 10, 2008 Jkt 217001 Any such differences are highlighted in a Note within the AD. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because of the possible failure of the rear engine mount on airplanes equipped with the incorrect barrel nuts, which could result in separation of the engine from the airplane and a consequent hazard to the airplane and persons and property on the ground. These incorrect rear engine mount barrel nuts may have been installed during maintenance on IAE Model V25xx-A5 series engines due to an error in the illustrated parts catalog. These incorrect barrel nuts cannot withstand the engine loads and must be replaced as soon as possible. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2008–1274; Directorate Identifier 2008–NM–197– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. 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, PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 75317 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 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 this AD: 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. 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: ■ 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2008–25–06 Airbus: Amendment 39–15764. Docket No. FAA–2008–1274; Directorate Identifier 2008–NM–197–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 26, 2008. E:\FR\FM\11DER1.SGM 11DER1 75318 Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A319–131, A319–132, A319–133, A320–231, A320–232, A320–233, A321–131, A321–231, and A321–232 series airplanes, certificated in any category; all serial numbers equipped with International Aero Engine (IAE) Model V2500–A1 engines or Model V25xx–A5 series engines. (The ‘‘xx’’ is used in the series engine reference to indicate various numbers listed in the type certificate data sheet.) Subject (d) Air Transport Association (ATA) of America Code 71: Powerplant. jlentini on PROD1PC65 with RULES Reason (e) The mandatory continued airworthiness information (MCAI) states: DGAC–France AD 90–079–009(B) R1 [and corresponding FAA AD 90–22–08, amendment 39–6781 (corrected on November 8, 1990, 55 FR 47028)] introduced an inspection and daily rectification action on Airbus A320–231 aircraft in order to prevent failure of one or more of the engine rear mount barrel nuts. Subsequent to the above problem, Airbus has advised that an incorrect part number has been introduced in the IPC (illustrated parts catalog) (reference 71–22–11 Figure 80B item 180) for the rear engine mount barrel nut. This problem affects Airbus A319, A320 and A321 models with IAE V2500–A5 engines. The part number introduced in error is not certificated for the IAE V2500–A5 engine installation and, if installed, may fail in service. This Airworthiness Directive (AD) * * * mandates the inspections required to determine the standard of barrel nut installed and the corrective actions, as necessary, for the aircraft with V2500–A1 or –A5 engines installed. Failure of the rear engine mount barrel nut could result in reduced structural integrity of the rear engine mount and possible separation of the engine from the airplane, and a consequent hazard to the airplane and persons and property on the ground. Required actions include inspecting for broken barrel nuts. The corrective actions include replacing the barrel nut with a different barrel nut and replacing the associated bolts, washers, and retainers; and contacting Airbus for corrective action if any affected barrel nut is found broken and doing that corrective action. Actions and Compliance (f) Unless already done, do the following actions for airplanes equipped with IAE model V2500–A1 engines: Within 7 days after the effective date of this AD, conduct a records review to determine if barrel nut part number (P/N) 83644–1612 is installed, in accordance with paragraph 5.1 of Airbus All Operator Telex (AOT) A320–71A1045, dated October 17, 2008. (1) For airplanes on which it can be positively determined from a records review that P/N 83644–1612 is not installed, no further action is required by this paragraph. VerDate Aug<31>2005 16:21 Dec 10, 2008 Jkt 217001 (2) For airplanes on which it cannot be positively determined from a records review that P/N 83644–1612 is not installed: Within 7 days after the effective date of this AD, do the visual inspections of the barrel nut for part numbers and for broken nuts in accordance with paragraph 5.2 of Airbus AOT A320–71A1045, dated October 17, 2008. (i) If one or more barrel nuts are found broken, before further flight contact Airbus for corrective actions and do the corrective actions. (ii) If two or more barrel nuts having P/N 83644–1612 are found installed, before further flight correct the installation in accordance with paragraph 5.2 of Airbus AOT A320–71A1045, dated October 17, 2008. (iii) If only one barrel nut having P/N 83644–1612 is found installed: At the later of the times specified in paragraphs (f)(1)(iii)(A) and (f)(2)(iii)(B) of this AD, correct the installation in accordance with paragraph 5.2 of Airbus AOT A320–71A1045, dated October 17, 2008. (A) Within 1,200 flight hours or 960 flight cycles since installation of the part, whichever occurs first. (B) Within 7 days after the effective date of this AD. (g) Unless already done, do the following actions for airplanes equipped with IAE Model V25xx–A5 series engines: Within 7 days after the effective date of this AD, conduct a records review to determine if barrel nut P/N 83644–1612 is installed, in accordance with paragraph 4.1 of Airbus AOT A320–71A1045, dated October 17, 2008. (1) For airplanes for which it can be positively determined from a records review that P/N 83644–1612 is not installed, no further action is required by this paragraph. (2) For airplanes on which it cannot be positively determined that P/N 83644–1612 is not installed: Within 7 days after the effective date of this AD, do the visual inspections of the barrel nut for part numbers and for broken nuts, in accordance with paragraph 4.2 of Airbus AOT A320–71A1045, dated October 17, 2008. (i) If one or more barrel nuts are found broken, before further flight contact Airbus for corrective actions and do the corrective actions. (ii) If two or more barrel nuts having P/N 83644–1612 are found installed, before further flight correct the installation in accordance with paragraph 4.2 of Airbus AOT A320–71A1045, dated October 17, 2008. (iii) If only one barrel nut having P/N 83644–1612 is found installed: At the later of the time specified in paragraphs (g)(2)(iii)(A) and (g)(2)(iii)(B) of this AD, correct the installation in accordance with paragraph 4.2 of Airbus AOT A320–71A1045, dated October 17, 2008. (A) Within 1,200 flight hours or 960 flight cycles since installation of the part, whichever occurs first. (B) Within 7 days after the effective date of this AD. (h) As of the effective date of this AD, no person may install an engine mount barrel PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 nut, part number 83644–1612, on any affected airplane. (i) Accomplishment of the corrective actions specified in paragraph (f) of this AD terminates the requirements of AD 90–22–08, amendment 39–6781. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (j) 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: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; 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 a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved 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. Related Information (k) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) Emergency Airworthiness Directive 2008–0191–E, dated October 20, 2008; and Airbus AOT A320– 71A1045, dated October 17, 2008; for related information. Material Incorporated by Reference (l) You must use Airbus All Operator Telex A320–71A1045, dated October 17, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the service information that is incorporated by reference E:\FR\FM\11DER1.SGM 11DER1 Federal Register / Vol. 73, No. 239 / Thursday, December 11, 2008 / Rules and Regulations at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 26, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–29182 Filed 12–10–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0732; Directorate Identifier 2008–NM–053–AD; Amendment 39–15762; AD 2008–25–04] RIN 2120–AA64 Airworthiness Directives; Dassault Model Mystere-Falcon 50 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: jlentini on PROD1PC65 with RULES * * * [S]ome aircraft could have experienced wing overpressure consecutive to the latent failure of both [pressure relief] valve units. Overpressure although not sufficient to cause static damages could have impaired the fatigue damage tolerance of the wing structure. * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 15, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 15, 2009. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the VerDate Aug<31>2005 16:21 Dec 10, 2008 Jkt 217001 U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 10, 2008 (73 FR 39628). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Analysed in-service events revealed that corrosion of pressure relief valves in wing fuel tanks was likely to occur well before reaching their Time Between Overhaul (TBO) and could make the valves stick in the closed position. Therefore some aircraft could have experienced wing overpressure consecutive to the latent failure of both valve units. Overpressure although not sufficient to cause static damages could have impaired the fatigue damage tolerance of the wing structure. Consequently this Airworthiness Directive (AD) mandates introduction of a new repetitive inspection of the wing structure. The repetitive ultrasonic inspection is intended to detect incipient cracking on the stiffeners of the right-hand and lefthand wing lower panels between ribs 13 and 17 (the inspection area extends to just beyond rib 16). The corrective actions if any cracking is found include contacting Dassault for repair instructions, and doing the repair. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request to Change the Inspection Interval for the ‘‘Valve Boxes’’ Jim Sparks, a private citizen, requests that a more practical solution to this subject would be to change the interval of inspections for the ‘‘valve boxes.’’ He states that the reliability of the ‘‘valve boxes’’ has not been stellar. The commenter explains that Model Mystere-Falcon 50 airplanes have two independent wing fuel tank ‘‘valve boxes’’ that incorporate over-pressure PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 75319 relief valves coupled with a stand-alone wing tank pressure reducing/ overpressure relief valve. The commenter states that because of the commonality in the system, both overpressure relief valves and the regulating valve would have to fail before any overpressure would occur. The commenter also states that the pressure relief valves, along with the entire system, do have manufacturer’s recommended intervals for both operational and functional testing and that a more practical solution would be to require a change to the inspection interval for those ‘‘valve boxes.’’ We disagree with the request to require a change to the repetitive inspection interval of the ‘‘valve boxes.’’ The purpose of this AD is to address the unsafe condition, which is possible damage to the wing structure due to over-pressurization. Therefore, we will be mandating only the inspections of the lower panel stiffeners. We are aware that the manufacturer has made changes to the design of the ‘‘valve boxes’’ and the inspection interval for them. We agree with the recommended changes from the manufacturer in modifying the design and inspection interval of the ‘‘valve boxes’’ and acknowledge that they could result in fewer overpressure occurrences leading to the unsafe condition of damage to the wing structure. However, the intent of this AD is to detect any cracking of the wing structure that might have a root cause in an overpressure event. We have not changed the AD in this regard. Explanation of Updated Service Information Since we issued the NPRM, Dassault has issued Falcon 50/50EX Maintenance Manual, Maintenance Procedure 57– 401, ‘‘Non-Destructive Check of the Wing Lower Panels Stiffeners Between Ribs 13 and 17 (ATA 57–00–21),’’ dated July 2008. (We referred to Temporary Revision 74, dated November 2007, to the Dassault Falcon 50/50EX Maintenance Manual, Maintenance Procedure 57–401, ‘‘Non-Destructive Check of the Wing Lower Panels Stiffeners Between Ribs 13 and 16 (ATA 57–00–21),’’ as the appropriate source of service information in the NPRM.) Maintenance Procedure 57–401, Revision July 2008, refers to ‘‘Between Ribs 13 and 17’’ rather than ‘‘Between Ribs 13 and 16.’’ The change to refer to Rib 17 and the corresponding change in certain sections of the maintenance procedure more accurately reflect the inspection area required by this AD and specified in the MCAI. We have revised paragraph (f) of this AD to include two separate paragraphs. E:\FR\FM\11DER1.SGM 11DER1

Agencies

[Federal Register Volume 73, Number 239 (Thursday, December 11, 2008)]
[Rules and Regulations]
[Pages 75316-75319]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-29182]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1274; Directorate Identifier 2008-NM-197-AD; 
Amendment 39-15764; AD 2008-25-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Series Airplanes Equipped With International Aero Engines (IAE) Model 
V2500-A1 Engines or Model V25xx-A5 Series Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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:

    * * * Airbus has advised that an incorrect part number has been 
introduced in the IPC (illustrated parts catalog) * * * for the rear 
engine mount barrel nut. This problem affects Airbus A319, A320 and 
A321 models with IAE (International Aero Engine) V2500-A5 engines.
    The part number introduced in error is not certificated for the 
IAE V2500-A5 engine installation and, if installed, may fail in 
service.
* * * * *

Failure of the rear engine mount barrel nut could result in reduced 
structural integrity of the rear engine mount and possible separation 
of the engine from the airplane, and a consequent hazard to the 
airplane and persons and property on the ground. This AD requires 
actions that are intended to address the unsafe condition described in 
the MCAI.

DATES: This AD becomes effective December 26, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 26, 
2008.
    We must receive comments on this AD by January 12, 2009.

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.

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 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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency Airworthiness Directive 2008-0191-E, dated October 20, 2008 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    DGAC-France AD 90-079-009(B) R1 [and corresponding FAA AD 90-22-
08, amendment 39-6781 (corrected on November 8, 1990, 55 FR 47028)] 
introduced an inspection and daily rectification action on Airbus 
A320-231 aircraft in order to prevent failure of one or more of the 
engine rear mount barrel nuts.
    Subsequent to the above problem, Airbus has advised that an 
incorrect part number has been introduced in the IPC (illustrated 
parts catalog) (reference 71-22-11 Figure 80B item 180) for the rear 
engine mount barrel nut. This problem affects Airbus A319, A320 and 
A321 models with IAE (International Aero Engine) V2500-A5 engines.

[[Page 75317]]

    The part number introduced in error is not certificated for the 
IAE V2500-A5 engine installation and, if installed, may fail in 
service.
    This Airworthiness Directive (AD), which supersedes DGAC-France 
AD 90-079-009(B) R1, mandates the inspections required to determine 
the standard of barrel nut installed and the corrective actions, as 
necessary, for the aircraft with V2500-A1 or -A5 engines installed.

Failure of the rear engine mount barrel nut could result in reduced 
structural integrity of the rear engine mount and possible separation 
of the engine from the airplane, and a consequent hazard to the 
airplane and persons and property on the ground. Required actions 
include inspecting for broken barrel nuts. The corrective actions 
include replacing the barrel nut with a different barrel nut and 
replacing the associated bolts, washers, and retainers; and contacting 
Airbus for corrective action if any affected barrel nut is found broken 
and doing that corrective action. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued All Operator Telex A320-71A1045, dated October 
17, 2008. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of this AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because of 
the possible failure of the rear engine mount on airplanes equipped 
with the incorrect barrel nuts, which could result in separation of the 
engine from the airplane and a consequent hazard to the airplane and 
persons and property on the ground. These incorrect rear engine mount 
barrel nuts may have been installed during maintenance on IAE Model 
V25xx-A5 series engines due to an error in the illustrated parts 
catalog. These incorrect barrel nuts cannot withstand the engine loads 
and must be replaced as soon as possible. Therefore, we determined that 
notice and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2008-1274; Directorate 
Identifier 2008-NM-197-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

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 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 this AD:
    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.

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 FAA amends Sec.  39.13 by adding the following new AD:

2008-25-06 Airbus: Amendment 39-15764. Docket No. FAA-2008-1274; 
Directorate Identifier 2008-NM-197-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
26, 2008.

[[Page 75318]]

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A319-131, A319-132, 
A319-133, A320-231, A320-232, A320-233, A321-131, A321-231, and 
A321-232 series airplanes, certificated in any category; all serial 
numbers equipped with International Aero Engine (IAE) Model V2500-A1 
engines or Model V25xx-A5 series engines. (The ``xx'' is used in the 
series engine reference to indicate various numbers listed in the 
type certificate data sheet.)

Subject

    (d) Air Transport Association (ATA) of America Code 71: 
Powerplant.

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:
    DGAC-France AD 90-079-009(B) R1 [and corresponding FAA AD 90-22-
08, amendment 39-6781 (corrected on November 8, 1990, 55 FR 47028)] 
introduced an inspection and daily rectification action on Airbus 
A320-231 aircraft in order to prevent failure of one or more of the 
engine rear mount barrel nuts.
    Subsequent to the above problem, Airbus has advised that an 
incorrect part number has been introduced in the IPC (illustrated 
parts catalog) (reference 71-22-11 Figure 80B item 180) for the rear 
engine mount barrel nut. This problem affects Airbus A319, A320 and 
A321 models with IAE V2500-A5 engines.
    The part number introduced in error is not certificated for the 
IAE V2500-A5 engine installation and, if installed, may fail in 
service.
    This Airworthiness Directive (AD) * * * mandates the inspections 
required to determine the standard of barrel nut installed and the 
corrective actions, as necessary, for the aircraft with V2500-A1 or 
-A5 engines installed.

Failure of the rear engine mount barrel nut could result in reduced 
structural integrity of the rear engine mount and possible 
separation of the engine from the airplane, and a consequent hazard 
to the airplane and persons and property on the ground. Required 
actions include inspecting for broken barrel nuts. The corrective 
actions include replacing the barrel nut with a different barrel nut 
and replacing the associated bolts, washers, and retainers; and 
contacting Airbus for corrective action if any affected barrel nut 
is found broken and doing that corrective action.

Actions and Compliance

    (f) Unless already done, do the following actions for airplanes 
equipped with IAE model V2500-A1 engines: Within 7 days after the 
effective date of this AD, conduct a records review to determine if 
barrel nut part number (P/N) 83644-1612 is installed, in accordance 
with paragraph 5.1 of Airbus All Operator Telex (AOT) A320-71A1045, 
dated October 17, 2008.
    (1) For airplanes on which it can be positively determined from 
a records review that P/N 83644-1612 is not installed, no further 
action is required by this paragraph.
    (2) For airplanes on which it cannot be positively determined 
from a records review that P/N 83644-1612 is not installed: Within 7 
days after the effective date of this AD, do the visual inspections 
of the barrel nut for part numbers and for broken nuts in accordance 
with paragraph 5.2 of Airbus AOT A320-71A1045, dated October 17, 
2008.
    (i) If one or more barrel nuts are found broken, before further 
flight contact Airbus for corrective actions and do the corrective 
actions.
    (ii) If two or more barrel nuts having P/N 83644-1612 are found 
installed, before further flight correct the installation in 
accordance with paragraph 5.2 of Airbus AOT A320-71A1045, dated 
October 17, 2008.
    (iii) If only one barrel nut having P/N 83644-1612 is found 
installed: At the later of the times specified in paragraphs 
(f)(1)(iii)(A) and (f)(2)(iii)(B) of this AD, correct the 
installation in accordance with paragraph 5.2 of Airbus AOT A320-
71A1045, dated October 17, 2008.
    (A) Within 1,200 flight hours or 960 flight cycles since 
installation of the part, whichever occurs first.
    (B) Within 7 days after the effective date of this AD.
    (g) Unless already done, do the following actions for airplanes 
equipped with IAE Model V25xx-A5 series engines: Within 7 days after 
the effective date of this AD, conduct a records review to determine 
if barrel nut P/N 83644-1612 is installed, in accordance with 
paragraph 4.1 of Airbus AOT A320-71A1045, dated October 17, 2008.
    (1) For airplanes for which it can be positively determined from 
a records review that P/N 83644-1612 is not installed, no further 
action is required by this paragraph.
    (2) For airplanes on which it cannot be positively determined 
that P/N 83644-1612 is not installed: Within 7 days after the 
effective date of this AD, do the visual inspections of the barrel 
nut for part numbers and for broken nuts, in accordance with 
paragraph 4.2 of Airbus AOT A320-71A1045, dated October 17, 2008.
    (i) If one or more barrel nuts are found broken, before further 
flight contact Airbus for corrective actions and do the corrective 
actions.
    (ii) If two or more barrel nuts having P/N 83644-1612 are found 
installed, before further flight correct the installation in 
accordance with paragraph 4.2 of Airbus AOT A320-71A1045, dated 
October 17, 2008.
    (iii) If only one barrel nut having P/N 83644-1612 is found 
installed: At the later of the time specified in paragraphs 
(g)(2)(iii)(A) and (g)(2)(iii)(B) of this AD, correct the 
installation in accordance with paragraph 4.2 of Airbus AOT A320-
71A1045, dated October 17, 2008.
    (A) Within 1,200 flight hours or 960 flight cycles since 
installation of the part, whichever occurs first.
    (B) Within 7 days after the effective date of this AD.
    (h) As of the effective date of this AD, no person may install 
an engine mount barrel nut, part number 83644-1612, on any affected 
airplane.
    (i) Accomplishment of the corrective actions specified in 
paragraph (f) of this AD terminates the requirements of AD 90-22-08, 
amendment 39-6781.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (j) 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: Tim 
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2141; 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 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.

Related Information

    (k) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) Emergency 
Airworthiness Directive 2008-0191-E, dated October 20, 2008; and 
Airbus AOT A320-71A1045, dated October 17, 2008; for related 
information.

Material Incorporated by Reference

    (l) You must use Airbus All Operator Telex A320-71A1045, dated 
October 17, 2008, to do the actions required by this AD, unless the 
AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; fax +33 5 61 93 44 51; e-mail: 
account.airworth-eas@airbus.com; Internet https://www.airbus.com.
    (3) You may review copies of the service information that is 
incorporated by reference

[[Page 75319]]

at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington. For information on the availability of this 
material at the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call (202) 741-6030, 
or go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on November 26, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-29182 Filed 12-10-08; 8:45 am]
BILLING CODE 4910-13-P
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