Airworthiness Directives; Airbus Airplanes, 70366-70369 [2012-28422]

Download as PDF 70366 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations DEPARTMENT OF TRANSPORTATION unsafe condition for the specified products. The MCAI states: Federal Aviation Administration Two operators of A330 aeroplanes fitted with Rolls-Royce Trent 700 engines reported finding extensive damage to engine air intake cowls as a result of acoustic panel collapse, most probably caused by panel disbonding. This condition, if not detected and corrected, could lead to the detachment of the engine air intake cowl from the engine, possibly resulting in ingestion of parts by, and consequence damage to, the engine, or injury to persons on the ground. For the reasons described above, this [European Aviation Safety Agency (EASA)] AD requires repetitive special detailed inspections (tap tests) of the 3 inner acoustic panels of both engine air intake cowls to detect any disbonding and, depending on findings, applicable corrective actions. 14 CFR Part 39 [Docket No. FAA–2012–0640; Directorate Identifier 2011–NM–203–AD; Amendment 39–17256; AD 2012–22–18] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330–243, –243F, –341, –342, and –343 airplanes equipped with Rolls-Royce Trent 700 engines. This AD was prompted by reports of extensive damage to engine air intake cowls as a result of acoustic panel collapse. This AD requires repetitive inspections of the three inner acoustic panels of both engine air intake cowls to detect disbonding, and corrective actions if necessary. We are issuing this AD to detect and correct disbonding, which could result in detachment of the engine air intake cowl from the engine leading to ingestion of parts, which could cause failure of the engine, and possible injury to persons on the ground. DATES: This AD becomes effective December 31, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 31, 2012. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: 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 June 21, 2012 (77 FR 37344). That NPRM proposed to correct an VerDate Mar<15>2010 16:35 Nov 23, 2012 Jkt 229001 The unsafe condition is detachment of the engine air intake cowl from the engine, which could result in ingestion of parts causing failure of the engine, and possible injury to persons on the ground. Corrective actions include repair or replacement of the affected engine air intake cowl. 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 comments received. Request To Change Unsafe Condition Statement Airbus stated that the MCAI does not refer to reduced controllability of the airplane as a potential consequence, but to injury to persons on the ground. We infer that the commenter requests that we modify the unsafe condition statement specified in the NPRM (77 FR 37344, June 21, 2012). We agree to change the unsafe condition statement in the AD to remove the reference to reduced airplane controllability. We have changed the AD accordingly. Request To Delete References to Airbus Service Information Appendices US Airways requested that we delete references to Appendices 01 and 02 of Airbus Mandatory Service Bulletin A330–71–3024, Revision 01, dated September 27, 2011, in paragraph (h) and in other locations of the NPRM (77 FR 37344, June 21, 2012). US Airways stated that Appendix 01 of Airbus Mandatory Service Bulletin A330–71– 3024, Revision 01, dated September 27, 2011, is simply a form that reports inspection results to Airbus, and it does not recommend mandating an administrative action that is related to the safety aspect of inspecting the inlet cowl. US Airways stated that accomplishing this reporting task is PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 burdensome and does not improve the safety aspects of the inlet cowl inspection. US Airways stated that Appendix 02 of Airbus Mandatory Service Bulletin A330–71–3024, Revision 01, dated September 27, 2011, is simply a Gantt chart outlining potential man hours and aircraft downtime needed to complete the inspection. We agree to clarify the AD. There are no references to Appendix 01 and/or Appendix 02 of Airbus Mandatory Service Bulletin A330–71–3024, Revision 01, dated September 27, 2011, in paragraph (h) or any other regulatory section of the AD. However, we have revised the references to this service information in paragraphs (g), (h), (l), and (m) of this AD to exclude Appendices 01 through 03, because the information provided in those appendices is not necessary to accomplish the requirements of this AD. We consider Appendix 03 of Airbus Mandatory Service Bulletin A330–71– 3024, Revision 01, dated September 27, 2011, unnecessary to accomplish the requirements of this AD, because it is a Gantt chart outlining elapsed time assumptions for the actions described in that service information. Request To Delete References to RollsRoyce Service Information Appendix US Airways requested that we state in the NPRM (77 FR 37344, June 21, 2012) that Appendix 1 of Rolls-Royce NonModification Service Bulletin RB.211– 71–AG419, Revision 1, dated May 10, 2011, does not need to be accomplished. US Airways stated that Appendix 1 of Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, dated May 10, 2011, noted that accomplishing of this service information should be marked on the engine air inlet cowl label plate and that Rolls-Royce and/or Bombardier should be notified of the inspection results. US Airways stated that it, and most other operators/carriers in the world, use an electronic database to issue, track, and record mandatory inspections on their airplanes, and, consequently, there is no need to mandate marking the inspection service information reference on the inlet cowl label plate. US Airways also stated that notification of a Rolls-Royce or Bombardier representative is burdensome and does not improve the safety aspects of the inlet cowl inspection. We partially agree. We do not agree to remove the reference to Appendix 1 of Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, dated May 10, 2011, because Item 1 of Appendix 1 specifies that E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations accomplishment of this service information should be marked on the engine air inlet cowl label plate using metal stamp, vibro etch, or electro etch on the engine air intake cowl modification plate. Not all operators use an electronic data base to track inspections. In case of the airplane transfer to another operator, this marking will ensure the evidence of the accomplishment of required actions. We agree that Items 2 and 3 of Appendix 1 of Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, dated May 10, 2011, which specify reporting, are not necessary. We have added new paragraph (j) to this AD to specify that the reporting specified in Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, is not required by this AD, and have re-identified subsequent paragraphs accordingly. We have also revised paragraph (i) of this AD to include the paragraph (j) exclusion. Request To Specify Revised Service Information US Airways requested that we revise paragraph (i) of the NPRM (77 FR 37344, June 21, 2012) to specify Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, as the correct service information. We agree to revise the reference to Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, to correctly identify that document as Revision 1. We have changed paragraphs (i)(1), (i)(1)(i), (i)(1)(ii), (i)(1)(iii), (i)(2), and (l)(1)(ii) (paragraph (k)(1)(ii) of the NPRM (77 FR 37344, June 21, 2012)), of the AD to correctly reference Rolls-Royce NonModification Service Bulletin RB.211– 71–AG419, Revision 1, including Appendix 1, dated May 10, 2011. mstockstill on DSK4VPTVN1PROD with RULES Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 37344, June 21, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 37344, June 21, 2012). VerDate Mar<15>2010 16:35 Nov 23, 2012 Jkt 229001 Costs of Compliance We estimate that this AD will affect 22 products of U.S. registry. We also estimate that it will take about 20 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $37,400, or $1,700 per product. In addition, we estimate that any necessary follow-on actions would take up to 34 work-hours, for a cost of $2,890 per product. We have received no definitive data that would enable us to provide parts cost estimates for the oncondition actions specified in this AD. We have no way of determining the number of products that may need these actions. 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 that 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); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 70367 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 the NPRM (77 FR 37344, June 21, 2012), 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. 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: ■ 2012–22–18 Airbus: Amendment 39–17256. Docket No. FAA–2012–0640; Directorate Identifier 2011–NM–203–AD. (a) Effective Date This airworthiness directive (AD) becomes effective December 31, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A330– 243, -243F, -341, -342, and -343 airplanes; certificated in any category; all manufacturer serial numbers; equipped with Rolls-Royce Trent 700 engines. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by reports of extensive damage to engine air intake cowls as a result of acoustic panel collapse. We are issuing this AD to detect and correct disbonding, which could result in detachment of the engine air intake cowl E:\FR\FM\26NOR1.SGM 26NOR1 70368 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations from the engine leading to ingestion of parts, which could cause failure of the engine, and possible injury to persons on the ground. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Repetitive Detailed Inspection At the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD: Do a tap test inspection of the three inner acoustic panels of each engine air intake cowl for disbonding, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–71– 3024, Revision 01, excluding Appendices 01 through 03, dated September 27, 2011. Repeat the inspection thereafter at intervals not to exceed 24 months, except as required by paragraphs (h) and (i) of this AD. (1) For an engine air intake cowl that has accumulated less than 5,000 total flight cycles or less than 20,000 total flight hours, whichever occurs first, since its first installation on an airplane as of the effective date of this AD: Within 24 months after the engine air intake cowl has accumulated 5,000 total flight cycles or 20,000 total flight hours, whichever occurs first, since its first installation on an airplane. (2) For an engine air intake cowl that has accumulated 5,000 or more total flight cycles or 20,000 or more total flight hours, whichever occurs first, since its first installation on an airplane as of the effective date of this AD: Within 24 months after the effective date of this AD. mstockstill on DSK4VPTVN1PROD with RULES (h) Inspection of Replaced Engine Air Intake Cowl For airplanes on which an engine air intake cowl is replaced after the effective date of this AD, at the applicable compliance time specified in paragraph (h)(1) or (h)(2) of this AD: Do a tap test inspection for disbonding of the three inner acoustic panels of the affected engine air intake cowl for disbonding, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–71–3024, Revision 01, excluding Appendices 01 through 03, dated September 27, 2011. Repeat the inspection thereafter at intervals not to exceed 24 months. (1) Within 24 months after the engine air intake cowl accumulates 5,000 total flight cycles or 20,000 total flight hours, whichever occurs first, since its first installation on any airplane, except as required by paragraph (h)(2) of this AD. (2) Before installation, if an engine air intake cowl has accumulated 5,000 or more total flight cycles or 20,000 or more total flight hours, whichever occurs first, since its first installation on any airplane, and which has not been inspected in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–71–3024, Revision 01, excluding Appendices 01 through 03, dated September 27, 2011, within the preceding 24 months. VerDate Mar<15>2010 16:35 Nov 23, 2012 Jkt 229001 (i) Corrective Actions (1) If any disbonding is found during any inspection required by this AD, and the findings are within the permitted allowable damage limits (ADLs) specified in RollsRoyce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, except as specified in paragraph (j) of this AD: Do the actions specified in paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD. (i) Repeat the tap test inspection required by paragraph (g) of this AD at the applicable inspection interval specified in Rolls-Royce Non-Modification Service Bulletin RB.211– 71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, except as specified in paragraph (j) of this AD, until the actions required by paragraph (i)(1)(ii) or (i)(1)(iii) of this AD are accomplished. (ii) Repair the affected engine air intake cowl before further flight, in accordance with the Accomplishment Instructions of RollsRoyce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, except as specified in paragraph (j) of this AD. Repeat the inspection specified in paragraph (g) of this AD thereafter at the applicable compliance time specified in paragraph (g) of this AD. (iii) Replace the affected engine air intake cowl before further flight, in accordance with the Accomplishment Instructions of RollsRoyce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, except as specified in paragraph (j) of this AD. Repeat the inspection specified in paragraph (g) of this AD thereafter at the applicable compliance time specified in paragraph (g) of this AD. (2) If any disbonding is found during any inspection required by this AD, and the findings are not within the permitted ADLs specified in Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, except as specified in paragraph (j) of this AD: Before further flight, replace the affected engine air intake cowl, in accordance with the Accomplishment Instructions of Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, except as specified in paragraph (j) of this AD. Repeat the inspection specified in paragraph (g) of this AD thereafter at the applicable compliance time specified in paragraph (g) of this AD. approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1138; fax (425) 227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (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. (l) Related Information (1) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011–0173, dated September 13, 2011, and the service information specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD, for related information. (i) Airbus Mandatory Service Bulletin A330–71–3024, Revision 01, excluding Appendices 01 through 03, dated September 27, 2011. (ii) Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011. (j) No Reporting Requirement Although Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (2) For Airbus service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.330-A3A40@airbus.com; Internet http://www.airbus.com. For Rolls-Royce service information identified in this AD, contact RollsRoyce plc, P.O. Box 31, Derby, DE24 8BJ, England; telephone 011 44 1332 242424; fax 011 44 1332 249936; Internet https://www.aeromanager.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. (k) Other FAA AD Provisions 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 (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Rules and Regulations (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Mandatory Service Bulletin A330–71–3024, Revision 01, excluding Appendices 01 through 03, dated September 27, 2011. (ii) Rolls-Royce Non-Modification Service Bulletin RB.211–71–AG419, Revision 1, including Appendix 1, dated May 10, 2011. (3) For Airbus service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. For Rolls-Royce service information identified in this AD, contact RollsRoyce plc, P.O. Box 31, Derby, DE24 8BJ, England; telephone 011 44 1332 242424; fax 011 44 1332 249936; Internet https://www.aeromanager.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference 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/cfr/ibr-locations.html. Issued in Renton, Washington, on October 31, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–28422 Filed 11–23–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0676; Directorate Identifier 2011–NM–182–AD; Amendment 39–17266; AD 2012–23–10] mstockstill on DSK4VPTVN1PROD with RULES RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all SUMMARY: VerDate Mar<15>2010 16:35 Nov 23, 2012 Jkt 229001 Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of the escape slide of the raft inflation system not deploying when activated due to the rotation of the cable guide in a direction which resulted in jamming of the inflation control cable. This AD requires modifying the affected slide rafts. We are issuing this AD to prevent nondeployment of the inflation system of the escape slide raft, which could result in delayed evacuation from the airplane during an emergency, and consequent injury to the passengers. DATES: This AD becomes effective December 31, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 31, 2012. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1405; 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 2, 2012 (77 FR 39186). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information (MCAI) states: Two occurrences on Airbus A320 aeroplanes have been reported where the escape slide raft inflation system did not deploy when activated, due to the rotation of the cable guide in a direction which resulted in jamming of the inflation control cable. Additionally, there has been one reported case where the system did not deploy properly due to a cracked inflation hose fitting. Investigation conducted by the slide raft manufacturer showed that the hose fitting could be subject to a bending moment if improperly packed. Subsequently, the hose fitting could separate from the reservoir and the inflation of the slide raft may be impaired. This condition, if not corrected, could delay the evacuation from the aeroplane in PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 70369 case of emergency, possibly resulting in injury to the occupants. For the reasons described above, this [European Aviation Safety Agency (EASA)] AD requires modification of the affected slide rafts or [optional] replacement thereof with modified units. * * * * * The modification includes installing a cable guide adaptor, an anti-rotation bracket, and a new hose assembly. You may obtain further information by examining the MCAI in the AD. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. United Airlines (UAL) supports the compliance time of 36 months after the effective date of this AD. Request To Clarify Concurrent Requirements UAL requested we highlight that Air Cruisers Service Bulletin S.B.A320 004– 25–85 has a concurrent requirement to accomplish Air Cruisers Service Bulletin S.B.A320 004–25–56. UAL stated that it would like to receive a confirmation that Air Cruisers Service Bulletin S.B.A320 004–25–56 must also be accomplished to comply with the proposed AD (77 FR 39186, July 2, 2012). We agree with UAL’s comment. For the optional replacement in paragraph (h) of this final rule, we have clarified that the concurrent requirement specified in paragraph 1.B. of Air Cruisers Service Bulletin S.B. A320 004–25–85, Revision 2, dated January 3, 2012, is necessary. We have revised paragraphs (h), (j)(1), and (j)(2) in this final rule accordingly. Request To Remove the Parts Installation Limitation in Paragraph (j)(1) of the Proposed AD (77 FR 39186, July 2, 2012) UAL requested that the parts installation limitation in paragraph (j)(1) of the proposed AD (77 FR 39186, July 2, 2012) be removed. UAL stated that the proposed requirement will remove the operator’s flexibility to replace a post-AD part number with a pre-AD part number prior to the AD limit. UAL stated that, after the proposed AD effective date, it agrees that any new slide-rafts released by the home shop should have the AD requirements incorporated to prevent unit on-wing installation beyond the AD limit, but not on the ones currently installed onwing. UAL stated that it believes the intent of the proposed AD is to eliminate pre-AD part numbers after 36 months of the effective date. E:\FR\FM\26NOR1.SGM 26NOR1

Agencies

[Federal Register Volume 77, Number 227 (Monday, November 26, 2012)]
[Rules and Regulations]
[Pages 70366-70369]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-28422]



[[Page 70366]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0640; Directorate Identifier 2011-NM-203-AD; 
Amendment 39-17256; AD 2012-22-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-243, -243F, -341, -342, and -343 airplanes equipped 
with Rolls-Royce Trent 700 engines. This AD was prompted by reports of 
extensive damage to engine air intake cowls as a result of acoustic 
panel collapse. This AD requires repetitive inspections of the three 
inner acoustic panels of both engine air intake cowls to detect 
disbonding, and corrective actions if necessary. We are issuing this AD 
to detect and correct disbonding, which could result in detachment of 
the engine air intake cowl from the engine leading to ingestion of 
parts, which could cause failure of the engine, and possible injury to 
persons on the ground.

DATES: This AD becomes effective December 31, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 31, 
2012.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1138; 
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 June 21, 2012 (77 FR 
37344). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Two operators of A330 aeroplanes fitted with Rolls-Royce Trent 
700 engines reported finding extensive damage to engine air intake 
cowls as a result of acoustic panel collapse, most probably caused 
by panel disbonding.
    This condition, if not detected and corrected, could lead to the 
detachment of the engine air intake cowl from the engine, possibly 
resulting in ingestion of parts by, and consequence damage to, the 
engine, or injury to persons on the ground.
    For the reasons described above, this [European Aviation Safety 
Agency (EASA)] AD requires repetitive special detailed inspections 
(tap tests) of the 3 inner acoustic panels of both engine air intake 
cowls to detect any disbonding and, depending on findings, 
applicable corrective actions.

The unsafe condition is detachment of the engine air intake cowl from 
the engine, which could result in ingestion of parts causing failure of 
the engine, and possible injury to persons on the ground. Corrective 
actions include repair or replacement of the affected engine air intake 
cowl. 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 comments received.

Request To Change Unsafe Condition Statement

    Airbus stated that the MCAI does not refer to reduced 
controllability of the airplane as a potential consequence, but to 
injury to persons on the ground.
    We infer that the commenter requests that we modify the unsafe 
condition statement specified in the NPRM (77 FR 37344, June 21, 2012). 
We agree to change the unsafe condition statement in the AD to remove 
the reference to reduced airplane controllability. We have changed the 
AD accordingly.

Request To Delete References to Airbus Service Information Appendices

    US Airways requested that we delete references to Appendices 01 and 
02 of Airbus Mandatory Service Bulletin A330-71-3024, Revision 01, 
dated September 27, 2011, in paragraph (h) and in other locations of 
the NPRM (77 FR 37344, June 21, 2012). US Airways stated that Appendix 
01 of Airbus Mandatory Service Bulletin A330-71-3024, Revision 01, 
dated September 27, 2011, is simply a form that reports inspection 
results to Airbus, and it does not recommend mandating an 
administrative action that is related to the safety aspect of 
inspecting the inlet cowl. US Airways stated that accomplishing this 
reporting task is burdensome and does not improve the safety aspects of 
the inlet cowl inspection. US Airways stated that Appendix 02 of Airbus 
Mandatory Service Bulletin A330-71-3024, Revision 01, dated September 
27, 2011, is simply a Gantt chart outlining potential man hours and 
aircraft downtime needed to complete the inspection.
    We agree to clarify the AD. There are no references to Appendix 01 
and/or Appendix 02 of Airbus Mandatory Service Bulletin A330-71-3024, 
Revision 01, dated September 27, 2011, in paragraph (h) or any other 
regulatory section of the AD. However, we have revised the references 
to this service information in paragraphs (g), (h), (l), and (m) of 
this AD to exclude Appendices 01 through 03, because the information 
provided in those appendices is not necessary to accomplish the 
requirements of this AD. We consider Appendix 03 of Airbus Mandatory 
Service Bulletin A330-71-3024, Revision 01, dated September 27, 2011, 
unnecessary to accomplish the requirements of this AD, because it is a 
Gantt chart outlining elapsed time assumptions for the actions 
described in that service information.

Request To Delete References to Rolls-Royce Service Information 
Appendix

    US Airways requested that we state in the NPRM (77 FR 37344, June 
21, 2012) that Appendix 1 of Rolls-Royce Non-Modification Service 
Bulletin RB.211-71-AG419, Revision 1, dated May 10, 2011, does not need 
to be accomplished. US Airways stated that Appendix 1 of Rolls-Royce 
Non-Modification Service Bulletin RB.211-71-AG419, Revision 1, dated 
May 10, 2011, noted that accomplishing of this service information 
should be marked on the engine air inlet cowl label plate and that 
Rolls-Royce and/or Bombardier should be notified of the inspection 
results. US Airways stated that it, and most other operators/carriers 
in the world, use an electronic database to issue, track, and record 
mandatory inspections on their airplanes, and, consequently, there is 
no need to mandate marking the inspection service information reference 
on the inlet cowl label plate. US Airways also stated that notification 
of a Rolls-Royce or Bombardier representative is burdensome and does 
not improve the safety aspects of the inlet cowl inspection.
    We partially agree. We do not agree to remove the reference to 
Appendix 1 of Rolls-Royce Non-Modification Service Bulletin RB.211-71-
AG419, Revision 1, dated May 10, 2011, because Item 1 of Appendix 1 
specifies that

[[Page 70367]]

accomplishment of this service information should be marked on the 
engine air inlet cowl label plate using metal stamp, vibro etch, or 
electro etch on the engine air intake cowl modification plate. Not all 
operators use an electronic data base to track inspections. In case of 
the airplane transfer to another operator, this marking will ensure the 
evidence of the accomplishment of required actions. We agree that Items 
2 and 3 of Appendix 1 of Rolls-Royce Non-Modification Service Bulletin 
RB.211-71-AG419, Revision 1, dated May 10, 2011, which specify 
reporting, are not necessary. We have added new paragraph (j) to this 
AD to specify that the reporting specified in Rolls-Royce Non-
Modification Service Bulletin RB.211-71-AG419, Revision 1, including 
Appendix 1, dated May 10, 2011, is not required by this AD, and have 
re-identified subsequent paragraphs accordingly. We have also revised 
paragraph (i) of this AD to include the paragraph (j) exclusion.

Request To Specify Revised Service Information

    US Airways requested that we revise paragraph (i) of the NPRM (77 
FR 37344, June 21, 2012) to specify Rolls-Royce Non-Modification 
Service Bulletin RB.211-71-AG419, Revision 1, including Appendix 1, 
dated May 10, 2011, as the correct service information.
    We agree to revise the reference to Rolls-Royce Non-Modification 
Service Bulletin RB.211-71-AG419, Revision 1, including Appendix 1, 
dated May 10, 2011, to correctly identify that document as Revision 1. 
We have changed paragraphs (i)(1), (i)(1)(i), (i)(1)(ii), (i)(1)(iii), 
(i)(2), and (l)(1)(ii) (paragraph (k)(1)(ii) of the NPRM (77 FR 37344, 
June 21, 2012)), of the AD to correctly reference Rolls-Royce Non-
Modification Service Bulletin RB.211-71-AG419, Revision 1, including 
Appendix 1, dated May 10, 2011.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 37344, June 21, 2012) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 37344, June 21, 2012).

Costs of Compliance

    We estimate that this AD will affect 22 products of U.S. registry. 
We also estimate that it will take about 20 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $37,400, or $1,700 per product.
    In addition, we estimate that any necessary follow-on actions would 
take up to 34 work-hours, for a cost of $2,890 per product. We have 
received no definitive data that would enable us to provide parts cost 
estimates for the on-condition actions specified in this AD. We have no 
way of determining the number of products that may need these actions.

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 that 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 the NPRM (77 FR 37344, June 21, 2012), 
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.

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

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:

2012-22-18 Airbus: Amendment 39-17256. Docket No. FAA-2012-0640; 
Directorate Identifier 2011-NM-203-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 31, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-243, -243F, -341, -342, and 
-343 airplanes; certificated in any category; all manufacturer 
serial numbers; equipped with Rolls-Royce Trent 700 engines.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of extensive damage to engine 
air intake cowls as a result of acoustic panel collapse. We are 
issuing this AD to detect and correct disbonding, which could result 
in detachment of the engine air intake cowl

[[Page 70368]]

from the engine leading to ingestion of parts, which could cause 
failure of the engine, and possible injury to persons on the ground.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Repetitive Detailed Inspection

    At the applicable compliance time specified in paragraph (g)(1) 
or (g)(2) of this AD: Do a tap test inspection of the three inner 
acoustic panels of each engine air intake cowl for disbonding, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-71-3024, Revision 01, excluding Appendices 01 
through 03, dated September 27, 2011. Repeat the inspection 
thereafter at intervals not to exceed 24 months, except as required 
by paragraphs (h) and (i) of this AD.
    (1) For an engine air intake cowl that has accumulated less than 
5,000 total flight cycles or less than 20,000 total flight hours, 
whichever occurs first, since its first installation on an airplane 
as of the effective date of this AD: Within 24 months after the 
engine air intake cowl has accumulated 5,000 total flight cycles or 
20,000 total flight hours, whichever occurs first, since its first 
installation on an airplane.
    (2) For an engine air intake cowl that has accumulated 5,000 or 
more total flight cycles or 20,000 or more total flight hours, 
whichever occurs first, since its first installation on an airplane 
as of the effective date of this AD: Within 24 months after the 
effective date of this AD.

(h) Inspection of Replaced Engine Air Intake Cowl

    For airplanes on which an engine air intake cowl is replaced 
after the effective date of this AD, at the applicable compliance 
time specified in paragraph (h)(1) or (h)(2) of this AD: Do a tap 
test inspection for disbonding of the three inner acoustic panels of 
the affected engine air intake cowl for disbonding, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-71-3024, Revision 01, excluding Appendices 01 through 
03, dated September 27, 2011. Repeat the inspection thereafter at 
intervals not to exceed 24 months.
    (1) Within 24 months after the engine air intake cowl 
accumulates 5,000 total flight cycles or 20,000 total flight hours, 
whichever occurs first, since its first installation on any 
airplane, except as required by paragraph (h)(2) of this AD.
    (2) Before installation, if an engine air intake cowl has 
accumulated 5,000 or more total flight cycles or 20,000 or more 
total flight hours, whichever occurs first, since its first 
installation on any airplane, and which has not been inspected in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-71-3024, Revision 01, excluding Appendices 01 
through 03, dated September 27, 2011, within the preceding 24 
months.

(i) Corrective Actions

    (1) If any disbonding is found during any inspection required by 
this AD, and the findings are within the permitted allowable damage 
limits (ADLs) specified in Rolls-Royce Non-Modification Service 
Bulletin RB.211-71-AG419, Revision 1, including Appendix 1, dated 
May 10, 2011, except as specified in paragraph (j) of this AD: Do 
the actions specified in paragraph (i)(1)(i), (i)(1)(ii), or 
(i)(1)(iii) of this AD.
    (i) Repeat the tap test inspection required by paragraph (g) of 
this AD at the applicable inspection interval specified in Rolls-
Royce Non-Modification Service Bulletin RB.211-71-AG419, Revision 1, 
including Appendix 1, dated May 10, 2011, except as specified in 
paragraph (j) of this AD, until the actions required by paragraph 
(i)(1)(ii) or (i)(1)(iii) of this AD are accomplished.
    (ii) Repair the affected engine air intake cowl before further 
flight, in accordance with the Accomplishment Instructions of Rolls-
Royce Non-Modification Service Bulletin RB.211-71-AG419, Revision 1, 
including Appendix 1, dated May 10, 2011, except as specified in 
paragraph (j) of this AD. Repeat the inspection specified in 
paragraph (g) of this AD thereafter at the applicable compliance 
time specified in paragraph (g) of this AD.
    (iii) Replace the affected engine air intake cowl before further 
flight, in accordance with the Accomplishment Instructions of Rolls-
Royce Non-Modification Service Bulletin RB.211-71-AG419, Revision 1, 
including Appendix 1, dated May 10, 2011, except as specified in 
paragraph (j) of this AD. Repeat the inspection specified in 
paragraph (g) of this AD thereafter at the applicable compliance 
time specified in paragraph (g) of this AD.
    (2) If any disbonding is found during any inspection required by 
this AD, and the findings are not within the permitted ADLs 
specified in Rolls-Royce Non-Modification Service Bulletin RB.211-
71-AG419, Revision 1, including Appendix 1, dated May 10, 2011, 
except as specified in paragraph (j) of this AD: Before further 
flight, replace the affected engine air intake cowl, in accordance 
with the Accomplishment Instructions of Rolls-Royce Non-Modification 
Service Bulletin RB.211-71-AG419, Revision 1, including Appendix 1, 
dated May 10, 2011, except as specified in paragraph (j) of this AD. 
Repeat the inspection specified in paragraph (g) of this AD 
thereafter at the applicable compliance time specified in paragraph 
(g) of this AD.

(j) No Reporting Requirement

    Although Rolls-Royce Non-Modification Service Bulletin RB.211-
71-AG419, Revision 1, including Appendix 1, dated May 10, 2011, 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(k) Other FAA AD Provisions

    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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (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.

(l) Related Information

    (1) Refer to MCAI European Aviation Safety Agency Airworthiness
    Directive 2011-0173, dated September 13, 2011, and the service 
information specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this 
AD, for related information.
    (i) Airbus Mandatory Service Bulletin A330-71-3024, Revision 01, 
excluding Appendices 01 through 03, dated September 27, 2011.
    (ii) Rolls-Royce Non-Modification Service Bulletin RB.211-71-
AG419, Revision 1, including Appendix 1, dated May 10, 2011.
    (2) For Airbus service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.330-A3A40@airbus.com; Internet http://www.airbus.com. For Rolls-Royce service information identified in this 
AD, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, England; 
telephone 011 44 1332 242424; fax 011 44 1332 249936; Internet https://www.aeromanager.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the incorporation 
by reference (IBR) of the service information listed in this paragraph 
under 5 U.S.C. 552(a) and 1 CFR part 51.

[[Page 70369]]

    (2) You must use this service information as applicable to do the 
actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A330-71-3024, Revision 01, 
excluding Appendices 01 through 03, dated September 27, 2011.
    (ii) Rolls-Royce Non-Modification Service Bulletin RB.211-71-AG419, 
Revision 1, including Appendix 1, dated May 10, 2011.
    (3) For Airbus service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. For Rolls-Royce service information identified in this 
AD, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, England; 
telephone 011 44 1332 242424; fax 011 44 1332 249936; Internet https://www.aeromanager.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.
    (5) You may view this service information that is incorporated by 
reference 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 31, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-28422 Filed 11-23-12; 8:45 am]
BILLING CODE 4910-13-P