Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes, 7804-7808 [E9-3276]

Download as PDF 7804 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations Board (MRB) Report MRB–145/1150. The initial compliance times for the tasks start from the initial delivery date of the applicable airplane at the applicable time specified in the tasks or within 200 flight cycles after revising the ALS, whichever occurs later. Repeat the applicable inspection thereafter at the interval specified in Embraer TR 10–5 of the Embraer EMB 145 MRB Report MRB–145/1150; except as provided by paragraphs (f)(2) and (g)(1) of this AD. Note 2: The actions required by paragraph (f)(1) of this AD may be done by inserting a copy of Embraer TR 10–5, dated May 23, 2007, into the sections. When this TR has been included in general revisions of the Embraer EMB 145 MRB Report MRB–145/ 1150, the general revisions may be inserted in the MRB report. (2) After accomplishing the actions specified in paragraph (f)(1) of this AD, no alternative inspections or inspection intervals may be used, except as provided by paragraph (g)(1) of this AD. FAA AD Differences Note 3: This AD differs from the MCAI and/or service information as follows: No differences. 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: Sanjay Ralhan, Aerospace Engineer, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1405; 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 (h) Refer to MCAI Brazilian Airworthiness Directive 2007–07–01, effective August 21, 2007; and Embraer TR 10–5, dated May 23, 2007, to the Embraer EMB145 MRB Report MRB–145/1150; for related information. Material Incorporated by Reference (i) You must use Embraer Temporary Revision 10–5, dated May 23, 2007, to the Embraer EMB145 Maintenance Review Board VerDate Nov<24>2008 16:40 Feb 19, 2009 Jkt 217001 Report MRB–145/1150, to do the actions required by this AD, unless the AD specifies otherwise. (Some pages of the document do not have the full document title.) (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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro ˜ Faria Lima, 2170—Putim—12227–901 Sao Jose dos Campos—SP—BRASIL; telephone: +55 12 3927–5852 or +55 12 3309–0732; fax: +55 12 3927–7546; e-mail: distrib@embraer.com.br; Internet: http:// www.flyembraer.com. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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: http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 4, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3274 Filed 2–19–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0657; Directorate Identifier 2007–NM–296–AD; Amendment 39–15787; AD 2009–01–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300, A310, and A300–600 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300, A310, and A300–600 series airplanes. That AD currently requires repetitive detailed visual inspections to detect cracks in the pylon thrust and sideload fitting of the wing, and replacement of any cracked pylon thrust and sideload fitting with a new fitting. This new AD reduces the threshold and repetitive intervals for the detailed inspection for certain airplanes and reduces the applicability of the existing AD. This AD results from issuance of PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective March 27, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 27, 2009. Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. 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: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 98–16–11, amendment 39–10687 (63 FR 40816, July 31, 1998). The existing AD applies to certain Airbus Model A300, A310, and A300– 600 series airplanes. That NPRM was published in the Federal Register on June 17, 2008 (73 FR 34224). That NPRM proposed to continue to require repetitive detailed visual inspections to detect cracks in the pylon thrust and sideload fitting of the wing, and replacement of any cracked pylon thrust and sideload fitting with a new fitting. That NPRM also proposed to require reducing the threshold and repetitive intervals for the detailed inspection for certain airplanes and would reduce the applicability of the existing AD. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received from the three commenters. E:\FR\FM\20FER1.SGM 20FER1 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations Request for Definition Paragraph An anonymous commenter requests that we revise the NPRM to add a ‘‘definitions’’ paragraph since Table 2 and Table 3 of the NPRM refer to both the long range and short range Model A310–300 series airplanes. The commenter suggests defining the average flight times. We do not agree. The Office of the Federal Register has approved the incorporation by reference of Airbus Mandatory Service Bulletin A310–57– 2075, Revision 03, dated December 1, 2006. Therefore, we have determined that it is not necessary to incorporate a definitions paragraph since paragraph 1.E. of this service bulletin includes an explanation of short-range and longrange airplanes, and their average flight times. We have not changed the final rule regarding this issue. Request To Mandate the Inspection Section of the Service Bulletins Air Transport Association, on behalf of American Airlines (AA), requests that, since the safety issue is detecting cracks in the fitting, the AD should mandate only the ‘‘inspection section’’ of Airbus Mandatory Service Bulletin A300–57–0232, Revision 02, dated February 21, 2000; Airbus Mandatory Service Bulletin A300–57–6079, Revision 04, dated February 21, 2000; and Airbus Mandatory Service Bulletin A310–57–2075, Revision 03, dated December 1, 2006; instead of the entire accomplishment instructions of these service bulletins. AA believes that mandating the ‘‘inspection section’’ would still correct the unsafe condition and allow operators to modify other steps as required, while maintaining a safe work environment. We disagree. We are mandating the entire Accomplishment Instructions of these service bulletins because they include the inspection, repair, and other necessary instructions to correct the unsafe condition. Affected operators may request approval for an alternative method of compliance, under the provisions of paragraph (k) of the AD. We have not changed the final rule regarding this issue. Request To Retain Inspection Requirements, Provide Terminating Action, and Provide Approval Authority FedEx Express requests that we include the following requirements in the NPRM: Keep the current inspection method and interval if the airplane has not reached the design service goal (the economic impact will increase due to additional inspections); terminate the VerDate Nov<24>2008 16:40 Feb 19, 2009 Jkt 217001 inspections if the pylon sideload fitting is replaced with a fitting made using improved manufacturing techniques; and provide an alternative means of compliance repair approval authority to the European Aviation Safety Agency (EASA) or its delegated agent. We disagree with keeping the current inspection method and interval for airplanes that have not reached the design service goal because we have determined that the new intervals are necessary to address the unsafe condition. We have not changed the final rule regarding this issue. We disagree with terminating the inspections if the pylon sideload fitting is replaced with a fitting made using improved manufacturing techniques. At this time we have not received sufficient information from the manufacturer or EASA to determine if the manufacturing techniques are adequate and the inspections can be terminated. We have not changed the final rule regarding this issue. We agree with FedEx Express that, as a method of compliance with paragraph (g) of this AD, repair approval authority can be given to EASA or its delegated agent. Affected operators may request an optional approval method, under the provisions of paragraph (j) of the AD. We have changed the final rule regarding this issue. Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD affects about 164 Model A300, A310, and A300–600 series airplanes of U.S. registry. The inspections that are required by AD 98– 16–11 and retained in this AD take about 3 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the currently required actions is $39,360, or $240 per airplane, per inspection cycle. 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 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 7805 detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment 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 Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–10687 (63 FR 40816, July 31, 1998) and by adding ■ E:\FR\FM\20FER1.SGM 20FER1 7806 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations the following new airworthiness directive (AD): 2009–01–08 Airbus: Amendment 39–15787. Docket No. FAA–2008–0657; Directorate Identifier 2007–NM–296–AD. Effective Date (a) This AD becomes effective March 27, 2009. Affected ADs (b) This AD supersedes AD 98–16–11. Applicability (c) This AD applies to Airbus airplanes identified in Table 1 of this AD, certificated in any category. TABLE 1—APPLICABILITY Model— As identified in Airbus Mandatory Service Bulletin— (1) A300 series airplanes ......................................................................... (2) A310 series airplanes ......................................................................... (3) A300–600 series airplanes ................................................................. A300–57–0232, Revision 02, dated February 21, 2000. A310–57–2075, Revision 03, dated December 1, 2006. A300–57–6079, Revision 04, dated February 21, 2000. Unsafe Condition (d) This AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity 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. Requirements of AD 98–16–11: Repetitive Detailed Inspections at Reduced Thresholds and Repeat Intervals for Certain Airplanes (f) At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Perform a detailed inspection to detect cracks in the pylon thrust and sideload fitting of the wing, in accordance with Airbus Service Bulletin A300–57–0232, Revision 01 (for Model A300 series airplanes); A310–57–2075, Revision 01 (for Model A310 series airplanes); or A300– 57–6079, Revision 02 (for Model A300–600 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraph (h) of this AD. (1) For Model A300 and A300–600 series airplanes: Inspect prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998 (the effective date AD 98–16–11), whichever occurs later, and thereafter at intervals not to exceed 2,800 flight cycles. (2) For Model A310 series airplanes: Inspect at the earlier of the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this AD. Repeat thereafter at the applicable intervals specified in Table 3 of this AD. (i) Prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998, whichever occurs later. (ii) At the applicable time specified in Table 2 of this AD. TABLE 2—REDUCED INSPECTION THRESHOLDS FOR MODEL A310 SERIES AIRPLANES Compliance time (whichever occurs later) Model Threshold A310–200 series airplanes. A310–300 series airplanes (short range). A310–300 series airplanes (long range). Grace period Before the accumulation of 1,500 total flight cycles or 3,000 total flight hours since first flight, whichever occurs first. Before the accumulation of 1,300 total flight cycles or 3,800 total flight hours since first flight, whichever occurs first. Before the accumulation of 800 total flight cycles or 4,000 total flight hours since first flight, whichever occurs first. Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. TABLE 3—REDUCED REPEAT INTERVALS FOR MODEL A310 SERIES AIRPLANES For Model— Repeat the detailed inspection at the later of— And, thereafter at intervals not to exceed— A310–200 series airplanes. Within 1,500 flight cycles or 3,000 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. Within 1,300 flight cycles or 3,800 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. Within 800 flight cycles or 4,000 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. 1,500 flight cycles or 3,000 flight hours, whichever occurs first. A310–300 series airplanes (short range). A310–300 series airplanes (long range). Corrective Action (g) If any crack is detected during any inspection required by paragraph (f) of this AD, prior to further flight, replace the pylon thrust and sideload fitting with a new fitting VerDate Nov<24>2008 17:40 Feb 19, 2009 Jkt 217001 1,300 flight cycles or 3,800 flight hours, whichever occurs first. 800 flight cycles or 4,000 flight hours, whichever occurs first. in accordance with Airbus Service Bulletin A300–57–0232, Revision 01 (for Model A300 series airplanes); A310–57–2075, Revision 01 (for Model A310 series airplanes); or A300– 57–6079, Revision 02 (for Model A300–600 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraphs (h) and (j) of this AD. E:\FR\FM\20FER1.SGM 20FER1 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations New Actions Required by This AD: Accomplishment Instructions of the applicable service bulletin specified in Table 4 of this AD to do the repetitive detailed inspections required by paragraph (f) of this New Service Information (h) For all airplanes: As of the effective date of this AD, use only the 7807 AD and the replacement required by paragraph (g) of this AD. TABLE 4—NEW SERVICE BULLETINS Airbus mandatory Service Bulletin— For model— (1) A300–57–0232, Revision 02, dated February 21, 2000 ............................................ (2) A300–57–6079, Revision 04, dated February 21, 2000 ............................................ (3) A310–57–2075, Revision 03, dated December 1, 2006 ............................................ A300 series airplanes. A300–600 series airplanes. A310 series airplanes. (i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300–57–6079, Revision 02, dated January 12, 1998, or Revision 03, dated October 25, 1999 (for Model A300–600 series airplanes); A310–57–2075, Revision 01, dated January 12, 1998, or Revision 02, dated February 21, 2000 (for Model A310 series airplanes); or A300–57–0232, Revision 01, dated January 12, 1998 (for Model A300 series airplanes); are acceptable for compliance with the corresponding requirements of this AD. Optional Approval Method (j) Repairing the pylon thrust and sideload fitting of the wing, using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA), or its delegated agent, is acceptable for compliance with the replacement required by paragraph (g) of this AD. 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. Alternative Methods of Compliance (AMOCs) (k) 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) Related Information (l) EASA airworthiness directive 2007– 0243, dated September 4, 2007, also addresses the subject of this AD. Material Incorporated by Reference (m) You must use service bulletins identified in Table 5 of this AD to do the actions required by this AD, as applicable, unless the AD specifies otherwise. TABLE 5—ALL MATERIAL INCORPORATED BY REFERENCE Airbus service information Airbus Airbus Airbus Airbus Airbus Airbus Revision Mandatory Service Bulletin A300–57–0232 ............................................................................ Mandatory Service Bulletin A300–57–6079 ............................................................................ Mandatory Service Bulletin A310–57–2075 ............................................................................ Service Bulletin A300–57–0232 .............................................................................................. Service Bulletin A300–57–6079 .............................................................................................. Service Bulletin A310–57–2075 .............................................................................................. (1) The Director of the Federal Register approved the incorporation by reference of the service bulletins identified in Table 6 of Date 02 04 03 01 02 01 February 21, 2000. February 21, 2000. December 1, 2006. January 12, 1998. January 12, 1998. January 12, 1998. this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 6—NEW MATERIAL INCORPORATED BY REFERENCE Airbus mandatory Service Bulletin— Revision— A300–57–0232 .................................................................................................................................... A300–57–6079 .................................................................................................................................... A310–57–2075 .................................................................................................................................... (2) On September 4, 1998 (63 FR 40816, July 31, 1998) the Director of the Federal Register approved the incorporation by Dated— 02 04 03 February 21, 2000. February 21, 2000. December 1, 2006. reference of the service bulletins identified in Table 7 of this AD. TABLE 7—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Airbus Service Bulletin— Revision— A300–57–0232 .................................................................................................................................... A310–57–2075 .................................................................................................................................... A300–57–6079 .................................................................................................................................... (3) For service information identified in this AD, contact Airbus SAS—EAW VerDate Nov<24>2008 16:40 Feb 19, 2009 Jkt 217001 (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 Dated— 01 01 02 January 12, 1998. January 12, 1998. January 12, 1998. telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth- E:\FR\FM\20FER1.SGM 20FER1 7808 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations eas@airbus.com; Internet http:// www.airbus.com. (4) 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. (5) 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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 18, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3276 Filed 2–19–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1205; Directorate Identifier 2008–CE–062–AD; Amendment 39–15811; AD 2009–04–05] RIN 2120–AA64 Airworthiness Directives; Cessna Aircraft Company Models 182Q and 182R Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 182Q and 182R airplanes that ´ are equipped with Societe de ´ Motorisations Aeronautiques (SMA) Aircraft Diesel Engine (ADE) Model SR305–230–1 or Model SR305–230 converted to Model SR305–230–1 installed under Supplemental Type Certificate (STC) SA03302AT. This AD requires you to remove the intercooler and the intercooler inlet and outlet hoses, install a reworked intercooler and new intercooler inlet and outlet hoses, inspect hoses and clamp torques, repetitively inspect installation of the intercooler outlet and inlet hose assemblies for any displacement or damage of clamps or hoses, and, if necessary, replace any damaged clamps or hoses. This AD results from a report of two instances of induction hose disconnection occurring while in service, resulting in a loss of turbo boost and a significant loss of engine power. We are issuing this AD to detect and correct improper intercooler outlet and intercooler inlet hose assembly installations, which could result in loss of turbo boost and a significant loss of engine power. This failure could lead to an inability to maintain constant altitude in flight. DATES: This AD becomes effective on March 27, 2009. On March 27, 2009, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: For service information identified in this AD, contact SMA Customer Service, 10–12 Rue Didier Daurat, 18021 Bourges, France; telephone: +33 (0) 2 48 67 56 00; fax: +33 (0) 2 48 50 01 41; E-mail: customer_services@smasr.com; Internet: http://www.smaengines.com. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http:// www.regulations.gov. The docket number is FAA–2008–1205; Directorate Identifier 2008–CE–062–AD. FOR FURTHER INFORMATION CONTACT: Don O. Young, Aerospace Engineer, ACE– 118A, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, Georgia 30349; telephone: (770) 703–6079; fax: (770) 703–6097. SUPPLEMENTARY INFORMATION: Discussion On November 6, 2008, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Cessna Models 182Q and 182R airplanes that are equipped with SMA ADE Model SR305–230–1 or Model SR305–230 converted to Model SR305– 230–1 installed under STC SA03302AT. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on November 13, 2008 (73 FR 67112). The NPRM proposed to require you to remove the intercooler and the intercooler inlet and outlet hoses, install a reworked intercooler and new intercooler inlet and outlet hoses, inspect hoses and clamp torques, repetitively inspect installation of the intercooler outlet and inlet hose assemblies for any displacement or damage of clamps or hoses, and, if necessary, replace any damaged clamps or hoses. Comments We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 7 airplanes in the U.S. registry. We estimate the following costs to do the replacements: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 4 work-hours × $80 per hour = $320 .......................................................................................... $3,436 $3,756 $26,292 We estimate the following costs to do any inspection of the installation of the intercooler hose assembly that would be required: Labor cost Parts cost Total cost per airplane 2 work-hours × $80 per hour = $160 ........................................................................... Not Applicable ........................................... $160 VerDate Nov<24>2008 16:40 Feb 19, 2009 Jkt 217001 PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 E:\FR\FM\20FER1.SGM 20FER1

Agencies

[Federal Register Volume 74, Number 33 (Friday, February 20, 2009)]
[Rules and Regulations]
[Pages 7804-7808]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3276]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-296-AD; 
Amendment 39-15787; AD 2009-01-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A310, and A300-600 
Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A300, A310, and A300-600 
series airplanes. That AD currently requires repetitive detailed visual 
inspections to detect cracks in the pylon thrust and sideload fitting 
of the wing, and replacement of any cracked pylon thrust and sideload 
fitting with a new fitting. This new AD reduces the threshold and 
repetitive intervals for the detailed inspection for certain airplanes 
and reduces the applicability of the existing AD. This AD results from 
issuance of mandatory continuing airworthiness information by a foreign 
civil airworthiness authority. We are issuing this AD to detect and 
correct cracks in the pylon thrust and sideload fitting of the wing, 
which could result in reduced structural integrity of the airplane.

DATES: This AD becomes effective March 27, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 27, 
2009.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

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:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 98-16-11, amendment 39-
10687 (63 FR 40816, July 31, 1998). The existing AD applies to certain 
Airbus Model A300, A310, and A300-600 series airplanes. That NPRM was 
published in the Federal Register on June 17, 2008 (73 FR 34224). That 
NPRM proposed to continue to require repetitive detailed visual 
inspections to detect cracks in the pylon thrust and sideload fitting 
of the wing, and replacement of any cracked pylon thrust and sideload 
fitting with a new fitting. That NPRM also proposed to require reducing 
the threshold and repetitive intervals for the detailed inspection for 
certain airplanes and would reduce the applicability of the existing 
AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the three commenters.

[[Page 7805]]

Request for Definition Paragraph

    An anonymous commenter requests that we revise the NPRM to add a 
``definitions'' paragraph since Table 2 and Table 3 of the NPRM refer 
to both the long range and short range Model A310-300 series airplanes. 
The commenter suggests defining the average flight times.
    We do not agree. The Office of the Federal Register has approved 
the incorporation by reference of Airbus Mandatory Service Bulletin 
A310-57-2075, Revision 03, dated December 1, 2006. Therefore, we have 
determined that it is not necessary to incorporate a definitions 
paragraph since paragraph 1.E. of this service bulletin includes an 
explanation of short-range and long-range airplanes, and their average 
flight times. We have not changed the final rule regarding this issue.

Request To Mandate the Inspection Section of the Service Bulletins

    Air Transport Association, on behalf of American Airlines (AA), 
requests that, since the safety issue is detecting cracks in the 
fitting, the AD should mandate only the ``inspection section'' of 
Airbus Mandatory Service Bulletin A300-57-0232, Revision 02, dated 
February 21, 2000; Airbus Mandatory Service Bulletin A300-57-6079, 
Revision 04, dated February 21, 2000; and Airbus Mandatory Service 
Bulletin A310-57-2075, Revision 03, dated December 1, 2006; instead of 
the entire accomplishment instructions of these service bulletins. AA 
believes that mandating the ``inspection section'' would still correct 
the unsafe condition and allow operators to modify other steps as 
required, while maintaining a safe work environment.
    We disagree. We are mandating the entire Accomplishment 
Instructions of these service bulletins because they include the 
inspection, repair, and other necessary instructions to correct the 
unsafe condition. Affected operators may request approval for an 
alternative method of compliance, under the provisions of paragraph (k) 
of the AD. We have not changed the final rule regarding this issue.

Request To Retain Inspection Requirements, Provide Terminating Action, 
and Provide Approval Authority

    FedEx Express requests that we include the following requirements 
in the NPRM: Keep the current inspection method and interval if the 
airplane has not reached the design service goal (the economic impact 
will increase due to additional inspections); terminate the inspections 
if the pylon sideload fitting is replaced with a fitting made using 
improved manufacturing techniques; and provide an alternative means of 
compliance repair approval authority to the European Aviation Safety 
Agency (EASA) or its delegated agent.
    We disagree with keeping the current inspection method and interval 
for airplanes that have not reached the design service goal because we 
have determined that the new intervals are necessary to address the 
unsafe condition. We have not changed the final rule regarding this 
issue.
    We disagree with terminating the inspections if the pylon sideload 
fitting is replaced with a fitting made using improved manufacturing 
techniques. At this time we have not received sufficient information 
from the manufacturer or EASA to determine if the manufacturing 
techniques are adequate and the inspections can be terminated. We have 
not changed the final rule regarding this issue.
    We agree with FedEx Express that, as a method of compliance with 
paragraph (g) of this AD, repair approval authority can be given to 
EASA or its delegated agent. Affected operators may request an optional 
approval method, under the provisions of paragraph (j) of the AD. We 
have changed the final rule regarding this issue.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the change described 
previously. We have determined that this change will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    This AD affects about 164 Model A300, A310, and A300-600 series 
airplanes of U.S. registry. The inspections that are required by AD 98-
16-11 and retained in this AD take about 3 work hours per airplane, at 
an average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the currently required actions is $39,360, or $240 
per airplane, per inspection cycle.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10687 (63 FR 40816, July 31, 1998) and by adding

[[Page 7806]]

the following new airworthiness directive (AD):

2009-01-08 Airbus: Amendment 39-15787. Docket No. FAA-2008-0657; 
Directorate Identifier 2007-NM-296-AD.

Effective Date

    (a) This AD becomes effective March 27, 2009.

Affected ADs

    (b) This AD supersedes AD 98-16-11.

Applicability

    (c) This AD applies to Airbus airplanes identified in Table 1 of 
this AD, certificated in any category.

                         Table 1--Applicability
------------------------------------------------------------------------
                                             As identified in Airbus
                Model--                    Mandatory Service Bulletin--
------------------------------------------------------------------------
(1) A300 series airplanes..............  A300-57-0232, Revision 02,
                                          dated February 21, 2000.
(2) A310 series airplanes..............  A310-57-2075, Revision 03,
                                          dated December 1, 2006.
(3) A300-600 series airplanes..........  A300-57-6079, Revision 04,
                                          dated February 21, 2000.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from issuance of mandatory continuing 
airworthiness information by a foreign civil airworthiness 
authority. We are issuing this AD to detect and correct cracks in 
the pylon thrust and sideload fitting of the wing, which could 
result in reduced structural integrity 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. Requirements of AD 98-16-11:

Repetitive Detailed Inspections at Reduced Thresholds and Repeat 
Intervals for Certain Airplanes

    (f) At the applicable time specified in paragraph (f)(1) or 
(f)(2) of this AD: Perform a detailed inspection to detect cracks in 
the pylon thrust and sideload fitting of the wing, in accordance 
with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model 
A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 
series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 
series airplanes); all dated January 12, 1998; as applicable; except 
as provided by paragraph (h) of this AD.
    (1) For Model A300 and A300-600 series airplanes: Inspect prior 
to the accumulation of 2,800 total flight cycles, or within 18 
months after September 4, 1998 (the effective date AD 98-16-11), 
whichever occurs later, and thereafter at intervals not to exceed 
2,800 flight cycles.
    (2) For Model A310 series airplanes: Inspect at the earlier of 
the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this 
AD. Repeat thereafter at the applicable intervals specified in Table 
3 of this AD.
    (i) Prior to the accumulation of 2,800 total flight cycles, or 
within 18 months after September 4, 1998, whichever occurs later.
    (ii) At the applicable time specified in Table 2 of this AD.

 Table 2--Reduced Inspection Thresholds for Model A310 Series Airplanes
------------------------------------------------------------------------
                               Compliance time (whichever occurs later)
            Model            -------------------------------------------
                                    Threshold           Grace period
------------------------------------------------------------------------
A310-200 series airplanes.    Before the            Within 800 flight
                               accumulation of       cycles or 1,600
                               1,500 total flight    flight hours after
                               cycles or 3,000       the effective date
                               total flight hours    of this AD,
                               since first flight,   whichever occurs
                               whichever occurs      first.
                               first.
A310-300 series airplanes     Before the            Within 800 flight
 (short range).                accumulation of       cycles or 1,600
                               1,300 total flight    flight hours after
                               cycles or 3,800       the effective date
                               total flight hours    of this AD,
                               since first flight,   whichever occurs
                               whichever occurs      first.
                               first.
A310-300 series airplanes     Before the            Within 800 flight
 (long range).                 accumulation of 800   cycles or 1,600
                               total flight cycles   flight hours after
                               or 4,000 total        the effective date
                               flight hours since    of this AD,
                               first flight,         whichever occurs
                               whichever occurs      first.
                               first.
------------------------------------------------------------------------


    Table 3--Reduced Repeat Intervals for Model A310 Series Airplanes
------------------------------------------------------------------------
                               Repeat the detailed   And, thereafter at
         For Model--            inspection at the     intervals not to
                                   later of--             exceed--
------------------------------------------------------------------------
A310-200 series airplanes.    Within 1,500 flight   1,500 flight cycles
                               cycles or 3,000       or 3,000 flight
                               flight hours since    hours, whichever
                               the last detailed     occurs first.
                               inspection,
                               whichever occurs
                               first; or within
                               800 flight cycles
                               or 1,600 flight
                               hours after the
                               effective date of
                               this AD, whichever
                               occurs first.
A310-300 series airplanes     Within 1,300 flight   1,300 flight cycles
 (short range).                cycles or 3,800       or 3,800 flight
                               flight hours since    hours, whichever
                               the last detailed     occurs first.
                               inspection,
                               whichever occurs
                               first; or within
                               800 flight cycles
                               or 1,600 flight
                               hours after the
                               effective date of
                               this AD, whichever
                               occurs first.
A310-300 series airplanes     Within 800 flight     800 flight cycles or
 (long range).                 cycles or 4,000       4,000 flight hours,
                               flight hours since    whichever occurs
                               the last detailed     first.
                               inspection,
                               whichever occurs
                               first; or within
                               800 flight cycles
                               or 1,600 flight
                               hours after the
                               effective date of
                               this AD, whichever
                               occurs first.
------------------------------------------------------------------------

Corrective Action

    (g) If any crack is detected during any inspection required by 
paragraph (f) of this AD, prior to further flight, replace the pylon 
thrust and sideload fitting with a new fitting in accordance with 
Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300 
series airplanes); A310-57-2075, Revision 01 (for Model A310 series 
airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series 
airplanes); all dated January 12, 1998; as applicable; except as 
provided by paragraphs (h) and (j) of this AD.

[[Page 7807]]

New Actions Required by This AD:

New Service Information

    (h) For all airplanes: As of the effective date of this AD, use 
only the Accomplishment Instructions of the applicable service 
bulletin specified in Table 4 of this AD to do the repetitive 
detailed inspections required by paragraph (f) of this AD and the 
replacement required by paragraph (g) of this AD.

                     Table 4--New Service Bulletins
------------------------------------------------------------------------
   Airbus mandatory Service Bulletin--              For model--
------------------------------------------------------------------------
(1) A300-57-0232, Revision 02, dated      A300 series airplanes.
 February 21, 2000.
(2) A300-57-6079, Revision 04, dated      A300-600 series airplanes.
 February 21, 2000.
(3) A310-57-2075, Revision 03, dated      A310 series airplanes.
 December 1, 2006.
------------------------------------------------------------------------

    (i) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-57-6079, Revision 02, 
dated January 12, 1998, or Revision 03, dated October 25, 1999 (for 
Model A300-600 series airplanes); A310-57-2075, Revision 01, dated 
January 12, 1998, or Revision 02, dated February 21, 2000 (for Model 
A310 series airplanes); or A300-57-0232, Revision 01, dated January 
12, 1998 (for Model A300 series airplanes); are acceptable for 
compliance with the corresponding requirements of this AD.

Optional Approval Method

    (j) Repairing the pylon thrust and sideload fitting of the wing, 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA), or its delegated agent, is acceptable 
for compliance with the replacement required by paragraph (g) of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (k) 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.

Related Information

    (l) EASA airworthiness directive 2007-0243, dated September 4, 
2007, also addresses the subject of this AD.

Material Incorporated by Reference

    (m) You must use service bulletins identified in Table 5 of this 
AD to do the actions required by this AD, as applicable, unless the 
AD specifies otherwise.

                                 Table 5--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
          Airbus service information              Revision                            Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A300-57-                 02  February 21, 2000.
 0232.
Airbus Mandatory Service Bulletin A300-57-                 04  February 21, 2000.
 6079.
Airbus Mandatory Service Bulletin A310-57-                 03  December 1, 2006.
 2075.
Airbus Service Bulletin A300-57-0232.........              01  January 12, 1998.
Airbus Service Bulletin A300-57-6079.........              02  January 12, 1998.
Airbus Service Bulletin A310-57-2075.........              01  January 12, 1998.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service bulletins identified in 
Table 6 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51.

                                 Table 6--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
     Airbus mandatory Service Bulletin--         Revision--                         Dated--
----------------------------------------------------------------------------------------------------------------
A300-57-0232.................................              02  February 21, 2000.
A300-57-6079.................................              04  February 21, 2000.
A310-57-2075.................................              03  December 1, 2006.
----------------------------------------------------------------------------------------------------------------

    (2) On September 4, 1998 (63 FR 40816, July 31, 1998) the 
Director of the Federal Register approved the incorporation by 
reference of the service bulletins identified in Table 7 of this AD.

                             Table 7--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
          Airbus Service Bulletin--              Revision--                         Dated--
----------------------------------------------------------------------------------------------------------------
A300-57-0232.................................              01  January 12, 1998.
A310-57-2075.................................              01  January 12, 1998.
A300-57-6079.................................              02  January 12, 1998.
----------------------------------------------------------------------------------------------------------------

    (3) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail: account.airworth-

[[Page 7808]]

eas@airbus.com; Internet http://www.airbus.com.
    (4) 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.
    (5) 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: http://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E9-3276 Filed 2-19-09; 8:45 am]
BILLING CODE 4910-13-P