Airworthiness Directives; The Boeing Company Airplanes, 72200-72203 [2012-29405]

Download as PDF 72200 Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations Rulemaking Procedure Because this amendment constitutes a minor technical correction to the NRC’s regulations and the authority citation for the prior technical corrections rulemaking, the Commission finds that the notice and comment provisions of the Administrative Procedure Act are unnecessary and is exercising its authority under 5 U.S.C. 553(b)(3)(B) to publish these amendments as a final rule. These amendments do not require action by any person or entity regulated by the NRC. Also, the final rule does not change the substantive responsibilities of any person or entity regulated by the NRC. Dated at Rockville, Maryland, this 29th day of November, 2012. Cindy Bladey, Chief, Rules, Announcements, and Directives Branch, Division of Administrative Services, Office of Administration. [FR Doc. 2012–29348 Filed 12–4–12; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1220; Directorate Identifier 2012–NM–208–AD; Amendment 39–17277; AD 2012–24–07] List of Subjects in 10 CFR Part 171 RIN 2120–AA64 Annual charges, Byproduct material, Holders of certificates, Registrations, Approvals, Intergovernmental relations, Non-payment penalties, Nuclear materials, Nuclear power plants and reactors, Source material, Special nuclear material. Airworthiness Directives; The Boeing Company Airplanes For the reasons set out in the preamble and under the authority of the Atomic Energy Act of 1954, as amended; the Energy Reorganization Act of 1974, as amended; and 5 U.S.C. 552 and 553, 10 CFR part 171 is corrected by making the following correcting amendment. PART 171—ANNUAL FEES FOR REACTOR LICENSES AND FUEL CYCLE LICENSES AND MATERIAL LICENSES, INCLUDING HOLDERS OF CERTIFICATES OF COMPLIANCE, REGISTRATIONS, AND QUALITY ASSURANCE PROGRAM APPROVALS AND GOVERNMENT AGENCIES LICENSED BY THE NRC 1. Revise the authority citation for part 171 to read as follows: tkelley on DSK3SPTVN1PROD with ■ Authority: Consolidated Omnibus Budget Reconciliation Act sec. 7601 Pub. L. 99–272, as amended by sec. 5601, Pub. L. 100–203 as amended by sec. 3201, Pub. L. 101–239, as amended by sec. 6101, Pub. L. 101–508, as amended by sec. 2903a, Pub. L. 102–486 (42 U.S.C. 2213, 2214), and as amended by Title IV, Pub. L. 109–103 (42 U.S.C. 2214); Atomic Energy Act sec. 161(w), 223, 234 (42 U.S.C. 2201(w), 2273, 2282); Energy Reorganization Act sec. 201 (42 U.S.C. 5841); Government Paperwork Elimination Act sec. 1704 (44 U.S.C. 3504 note); Energy Policy Act of 2005 sec. 651(e), Pub. L. 109–58 (42 U.S.C. 2014, 2021, 2021b, 2111). For the Nuclear Regulatory Commission. VerDate Mar<15>2010 16:02 Dec 04, 2012 Jkt 229001 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This AD requires ensuring that lockwire is installed correctly on the engine fuel feed manifold couplings. This AD also requires inspecting the assembly of the engine fuel feed manifold rigid and full flexible couplings. This AD was prompted by reports of fuel leaks due to improperly assembled engine fuel feed manifold couplings. We are issuing this AD to detect and correct improperly assembled couplings, which could result in fuel leaks and consequent fuel exhaustion, engine power loss or shutdown, or leaks on hot engine parts that could lead to a fire. DATES: This AD is effective December 5, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 5, 2012. We must receive comments on this AD by January 22, 2013. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. SUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H– 65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206– 766–5680; Internet https:// www.myboeingfleet.com. You may review copies of the referenced service information 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sherry Vevea, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6514; fax: 425–917–6590; email: sherry.vevea@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We have received reports of fuel leaks on two different in-service airplanes, and the subsequent discovery of several improperly assembled engine fuel feed manifold couplings on in-service and production airplanes. The improper coupling installations, which occurred during production, have included couplings with missing or improperly installed lockwire, parts within the couplings installed in the wrong locations, incorrect parts installed in the couplings, and couplings that have extra parts installed. These conditions, if not corrected, could result in fuel leaks, which could lead to fuel exhaustion, engine power loss or shutdown, or leaks on hot engine parts that could lead to a fire. E:\FR\FM\05DER1.SGM 05DER1 Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations Relevant Service Information We reviewed Boeing Multi Operator Message MOM–MOM–12–0838– 01B(R2), including Attachment A, dated November 25, 2012. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for Docket No. FAA–2012–1220. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the AD and the Service Information.’’ The phrase ‘‘related investigative actions’’ might be used in this AD. ‘‘Related investigative actions’’ are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. In addition, the phrase ‘‘corrective actions’’ might be used in this AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between the AD and the Service Information For engine fuel feed manifold couplings that have not been previously inspected, Boeing Multi Operator Message MOM–MOM–12–0838– 01B(R2), including Attachment A, dated November 25, 2012, recommends accomplishment of all actions specified in Action 1) within 7 days. This AD, however, requires only that operators ensure the correct lockwire installation within 7 days; the compliance time for the remaining actions is 21 days. We have determined that the additional time for the remaining actions is warranted, based on the assurance that the lockwire is installed correctly. In addition, for engine fuel feed manifold full flexible couplings that have been previously inspected, Boeing Multi Operator Message MOM–MOM– 12–0838–01B(R2), including Attachment A, dated November 25, 2012, specifies that operators do not need to re-inspect these couplings if review of the airplane maintenance records conclusively demonstrates that the corresponding actions are equivalent to steps 1 through 6 of Action 1) of Boeing Multi Operator Message MOM– MOM–12–0838–01B(R2), including Attachment A, dated November 25, 2012. We have determined that the potential for not identifying incorrect parts during prior inspection of the full flexible coupling warrants re-inspecting these couplings; this AD therefore requires inspection of these full flexible couplings. These differences have been coordinated with Boeing. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because improperly assembled 72201 engine fuel feed manifold couplings could result in fuel leaks and consequent fuel exhaustion, engine power loss or shutdown, or leaks on hot engine parts that could lead to a fire. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2012–1220 and Directorate Identifier 2012–NM–208–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 3 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Coupling inspection, o-ring replacement, retainer ring installation, blade seal inspection, and lockwire installation. 10 work-hours × $85 per hour = $850. $54 $904 $2,712 We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. tkelley on DSK3SPTVN1PROD with 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 VerDate Mar<15>2010 16:02 Dec 04, 2012 Jkt 229001 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings 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 E:\FR\FM\05DER1.SGM 05DER1 72202 Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations 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), (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. 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 airworthiness directive (AD): ■ 2012–24–07 The Boeing Company: Amendment 39–17277; Docket No. FAA–2012–1220; Directorate Identifier 2012–NM–208–AD. (a) Effective Date This AD is effective December 5, 2012. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787–8 airplanes, certificated in any category, serial numbers 34485, 34486, 34488, 34490, 34493, 34494, 34497, 34502, 34506 through 34508 inclusive, 34514, 34515, 34521, 34744 through 34747 inclusive, 34822, 34824, 34829, 34832, 34834 through 34838 inclusive, 35938, 36276 through 36278 inclusive, 38319, 38320, 38330, 38466, 38471, 40748, and 40899. tkelley on DSK3SPTVN1PROD with (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 28, Fuel. (e) Unsafe Condition This AD was prompted by reports of fuel leaks due to improperly assembled engine fuel feed manifold couplings. We are issuing this AD to detect and correct improperly VerDate Mar<15>2010 16:02 Dec 04, 2012 Jkt 229001 assembled couplings, which could result in fuel leaks and consequent fuel exhaustion, engine power loss or shutdown, or leaks on hot engine parts that could lead to a fire. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Except as provided by paragraph (h) of this AD: Do the actions specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with Action 1) of Boeing Multi Operator Message MOM–MOM–12–0838–01B(R2), including Attachment A, dated November 25, 2012. (1) Within 7 days after the effective date of this AD, ensure that the lockwire installation on the rigid and full flexible couplings is correct. (2) Within 21 days after the effective date of this AD, inspect the rigid and full flexible couplings for correct assembly, including replacement of the o-rings with new o-rings, confirmation that the proper retainer rings are installed in the full flexible coupling, a general visual inspection for damage of the blade seals, and all applicable corrective actions. Do all applicable corrective actions before further flight. (h) Requirements Based on Previous Accomplishment (1) For airplanes on which the fuel couplings have been inspected before the effective date of this AD as specified in ‘‘Method 1: AMM Method’’ of Boeing Multi Operator Message MOM–MOM–12–0838– 01B, dated November 11, 2012, which is not incorporated by reference in this AD; or Boeing Multi Operator Message MOM– MOM–12–0838–01B(R1), dated November 14, 2012, which is not incorporated by reference in this AD: A review of the airplane maintenance records is acceptable for compliance with the requirements of paragraph (g)(1) of this AD, if the records conclusively demonstrate that lockwire was installed correctly using a method equivalent to step 6.a. of Action 1) of Boeing Multi Operator Message MOM–MOM–12–0838– 01B(R2), including Attachment A, dated November 25, 2012. (2) For airplanes on which the fuel couplings have been inspected before the effective date of this AD as specified in ‘‘Method 2: Non-Invasive Method’’ of Boeing Multi Operator Message MOM–MOM–12– 0838–01B, dated November 11, 2012, which is not incorporated by reference in this AD; or Boeing Multi Operator Message MOM– MOM–12–0838–01B(R1), dated November 14, 2012, which is not incorporated by reference in this AD: The actions specified in paragraph (g)(1) of this AD are not required. (3) For airplanes on which the rigid fuel couplings have been inspected before the effective date of this AD as specified in ‘‘Method 1: AMM Method’’ or ‘‘Method 2: Non-Invasive Method’’ of Boeing Multi Operator Message MOM–MOM–12–0838– 01B, dated November 11, 2012, which is not incorporated by reference in this AD; or Boeing Multi Operator Message MOM– MOM–12–0838–01B(R1), dated November PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 14, 2012, which is not incorporated by reference in this AD: The actions specified in paragraph (g)(2) of this AD are not required for the rigid fuel couplings only. However, the actions specified in paragraph (g)(2) of this AD are required for the full flexible couplings, even if inspected prior to the effective date of this AD as specified in Boeing Multi Operator Message MOM– MOM–12–0838–01B, dated November 11, 2012, which is not incorporated by reference in this AD; or Boeing Multi Operator Message MOM–MOM–12–0838–01B(R1), dated November 14, 2012, which is not incorporated by reference in this AD. (i) No Reporting Requirement Boeing Multi Operator Message MOM– MOM–12–0838–01B(R2), including Attachment A, dated November 25, 2012, specifies reporting to Boeing any anomalies found during inspection of the assembly of the rigid and full flexible couplings, including anomalies of the lockwire installation. This AD does not require any report. (j) Special Flight Permit Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified, provided the lockwire is correctly installed on the engine fuel feed manifold rigid and full flexible couplings in accordance with paragraph (g)(1) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (l) Related Information (1) For more information about this AD, contact Sherry Vevea, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6514; fax: 425–917–6590; email: sherry.vevea@faa.gov. E:\FR\FM\05DER1.SGM 05DER1 Federal Register / Vol. 77, No. 234 / Wednesday, December 5, 2012 / Rules and Regulations (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information 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. (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. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Multi Operator Message MOM– MOM–12–0838–01B(R2), including Attachment A, dated November 25, 2012. The document number and issue date are identified on page 1 of Boeing Multi Operator Message MOM–MOM–12–0838–01B(R2), including Attachment A, dated November 25, 2012, and on each page of Attachment A; no other page of this document contains this information. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at 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. (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 https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on November 28, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–29405 Filed 12–4–12; 8:45 am] tkelley on DSK3SPTVN1PROD with BILLING CODE 4910–13–P VerDate Mar<15>2010 16:02 Dec 04, 2012 Jkt 229001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1245; Directorate Identifier 2012–NE–41–AD; Amendment 39– 17279; AD 2012–24–09] RIN 2120–AA64 Airworthiness Directives; Lycoming Engines and Continental Motors, Inc. Reciprocating Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Lycoming Engines TSIO–540–AK1A, and Continental Motors, Inc. TSIO–360– MB, TSIO–360–SB, and TSIO–360–RB reciprocating engines, with certain Hartzell Engine Technologies (HET) turbochargers, model TA0411, part number (P/N) 466642–0001; 466642– 0002; 466642–0006; 466642–9001; 466642–9002; or 466642–9006, or with certain HET model TA0411 turbochargers overhauled or repaired since August 29, 2012. This AD requires removing the affected turbochargers from service before further flight. This AD was prompted by a report of a turbocharger turbine wheel that failed a static strength test at its manufacturing facility. We are issuing this AD to prevent turbocharger turbine wheel failure, reduction or complete loss of engine power, loss of engine oil, oil fire, and damage to the airplane. DATES: This AD is effective December 20, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 20, 2012. We must receive comments on this AD by January 22, 2013. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., SUMMARY: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 72203 Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Hartzell Engine Technologies, LLC, 2900 Selma Highway, Montgomery, AL 36108, phone: 334–386–5400; fax: 334–386– 5450; internet: https:// www.hartzellenginetech.com. You may view this service information at the FAA, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Christopher Richards, Aerospace Engineer, Chicago Aircraft Certification Office, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847–294– 7156; fax: 847–294–7834; email: christopher.j.richards@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We received a report of an HET turbocharger turbine wheel that failed a static strength test at its manufacturing facility. Subsequent tests showed that nearly all turbine wheels, P/N 410188– 0019, had significant cracking under the surface of a critical weld joint between the turbine wheel head and shaft that occurred during manufacturing. HET has identified by serial number (S/N) the turbochargers shipped from the factory with this unsafe condition. HET has also identified the S/N range of affected turbine wheels. Some of the affected turbine wheels became available for overhaul or field repair since August 29, 2012, and may have been installed. This condition, if not corrected, could result in turbocharger turbine wheel failure, reduction or complete loss of engine power, loss of engine oil, oil fire, and damage to the airplane. Relevant Service Information We reviewed HET Alert Service Bulletin (ASB) No. 048, dated November 16, 2012. The ASB lists the known serial numbers of affected turbochargers. E:\FR\FM\05DER1.SGM 05DER1

Agencies

[Federal Register Volume 77, Number 234 (Wednesday, December 5, 2012)]
[Rules and Regulations]
[Pages 72200-72203]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-29405]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1220; Directorate Identifier 2012-NM-208-AD; 
Amendment 39-17277; AD 2012-24-07]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 787-8 airplanes. This AD requires ensuring 
that lockwire is installed correctly on the engine fuel feed manifold 
couplings. This AD also requires inspecting the assembly of the engine 
fuel feed manifold rigid and full flexible couplings. This AD was 
prompted by reports of fuel leaks due to improperly assembled engine 
fuel feed manifold couplings. We are issuing this AD to detect and 
correct improperly assembled couplings, which could result in fuel 
leaks and consequent fuel exhaustion, engine power loss or shutdown, or 
leaks on hot engine parts that could lead to a fire.

DATES: This AD is effective December 5, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 5, 
2012.
    We must receive comments on this AD by January 22, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P. O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 
You may review copies of the referenced service information 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.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Sherry Vevea, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6514; fax: 425-917-6590; email: sherry.vevea@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We have received reports of fuel leaks on two different in-service 
airplanes, and the subsequent discovery of several improperly assembled 
engine fuel feed manifold couplings on in-service and production 
airplanes. The improper coupling installations, which occurred during 
production, have included couplings with missing or improperly 
installed lockwire, parts within the couplings installed in the wrong 
locations, incorrect parts installed in the couplings, and couplings 
that have extra parts installed. These conditions, if not corrected, 
could result in fuel leaks, which could lead to fuel exhaustion, engine 
power loss or shutdown, or leaks on hot engine parts that could lead to 
a fire.

[[Page 72201]]

Relevant Service Information

    We reviewed Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2), 
including Attachment A, dated November 25, 2012. For information on the 
procedures and compliance times, see this service information at https://www.regulations.gov by searching for Docket No. FAA-2012-1220.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the AD and the Service Information.''
    The phrase ``related investigative actions'' might be used in this 
AD. ``Related investigative actions'' are follow-on actions that (1) 
are related to the primary actions, and (2) further investigate the 
nature of any condition found. Related investigative actions in an AD 
could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this AD. ``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Differences Between the AD and the Service Information

    For engine fuel feed manifold couplings that have not been 
previously inspected, Boeing Multi Operator Message MOM-MOM-12-0838-
01B(R2), including Attachment A, dated November 25, 2012, recommends 
accomplishment of all actions specified in Action 1) within 7 days. 
This AD, however, requires only that operators ensure the correct 
lockwire installation within 7 days; the compliance time for the 
remaining actions is 21 days. We have determined that the additional 
time for the remaining actions is warranted, based on the assurance 
that the lockwire is installed correctly.
    In addition, for engine fuel feed manifold full flexible couplings 
that have been previously inspected, Boeing Multi Operator Message MOM-
MOM-12-0838-01B(R2), including Attachment A, dated November 25, 2012, 
specifies that operators do not need to re-inspect these couplings if 
review of the airplane maintenance records conclusively demonstrates 
that the corresponding actions are equivalent to steps 1 through 6 of 
Action 1) of Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2), 
including Attachment A, dated November 25, 2012. We have determined 
that the potential for not identifying incorrect parts during prior 
inspection of the full flexible coupling warrants re-inspecting these 
couplings; this AD therefore requires inspection of these full flexible 
couplings.
    These differences have been coordinated with Boeing.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
improperly assembled engine fuel feed manifold couplings could result 
in fuel leaks and consequent fuel exhaustion, engine power loss or 
shutdown, or leaks on hot engine parts that could lead to a fire. 
Therefore, we find that notice and opportunity for prior public comment 
are impracticable and that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2012-1220 and 
Directorate Identifier 2012-NM-208-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 3 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Coupling inspection, o[dash]ring      10 work-hours x $85 per             $54             $904           $2,712
 replacement, retainer ring            hour = $850.
 installation, blade seal
 inspection, and lockwire
 installation.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

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

Regulatory Findings

    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

[[Page 72202]]

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),
    (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.

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 airworthiness 
directive (AD):

2012-24-07 The Boeing Company: Amendment 39-17277; Docket No. FAA-
2012-1220; Directorate Identifier 2012-NM-208-AD.

(a) Effective Date

    This AD is effective December 5, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes, 
certificated in any category, serial numbers 34485, 34486, 34488, 
34490, 34493, 34494, 34497, 34502, 34506 through 34508 inclusive, 
34514, 34515, 34521, 34744 through 34747 inclusive, 34822, 34824, 
34829, 34832, 34834 through 34838 inclusive, 35938, 36276 through 
36278 inclusive, 38319, 38320, 38330, 38466, 38471, 40748, and 
40899.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 28, Fuel.

(e) Unsafe Condition

    This AD was prompted by reports of fuel leaks due to improperly 
assembled engine fuel feed manifold couplings. We are issuing this 
AD to detect and correct improperly assembled couplings, which could 
result in fuel leaks and consequent fuel exhaustion, engine power 
loss or shutdown, or leaks on hot engine parts that could lead to a 
fire.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection

    Except as provided by paragraph (h) of this AD: Do the actions 
specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance 
with Action 1) of Boeing Multi Operator Message MOM-MOM-12-0838-
01B(R2), including Attachment A, dated November 25, 2012.
    (1) Within 7 days after the effective date of this AD, ensure 
that the lockwire installation on the rigid and full flexible 
couplings is correct.
    (2) Within 21 days after the effective date of this AD, inspect 
the rigid and full flexible couplings for correct assembly, 
including replacement of the o-rings with new o-rings, confirmation 
that the proper retainer rings are installed in the full flexible 
coupling, a general visual inspection for damage of the blade seals, 
and all applicable corrective actions. Do all applicable corrective 
actions before further flight.

(h) Requirements Based on Previous Accomplishment

    (1) For airplanes on which the fuel couplings have been 
inspected before the effective date of this AD as specified in 
``Method 1: AMM Method'' of Boeing Multi Operator Message MOM-MOM-
12-0838-01B, dated November 11, 2012, which is not incorporated by 
reference in this AD; or Boeing Multi Operator Message MOM-MOM-12-
0838-01B(R1), dated November 14, 2012, which is not incorporated by 
reference in this AD: A review of the airplane maintenance records 
is acceptable for compliance with the requirements of paragraph 
(g)(1) of this AD, if the records conclusively demonstrate that 
lockwire was installed correctly using a method equivalent to step 
6.a. of Action 1) of Boeing Multi Operator Message MOM-MOM-12-0838-
01B(R2), including Attachment A, dated November 25, 2012.
    (2) For airplanes on which the fuel couplings have been 
inspected before the effective date of this AD as specified in 
``Method 2: Non-Invasive Method'' of Boeing Multi Operator Message 
MOM-MOM-12-0838-01B, dated November 11, 2012, which is not 
incorporated by reference in this AD; or Boeing Multi Operator 
Message MOM-MOM-12-0838-01B(R1), dated November 14, 2012, which is 
not incorporated by reference in this AD: The actions specified in 
paragraph (g)(1) of this AD are not required.
    (3) For airplanes on which the rigid fuel couplings have been 
inspected before the effective date of this AD as specified in 
``Method 1: AMM Method'' or ``Method 2: Non-Invasive Method'' of 
Boeing Multi Operator Message MOM-MOM-12-0838-01B, dated November 
11, 2012, which is not incorporated by reference in this AD; or 
Boeing Multi Operator Message MOM-MOM-12-0838-01B(R1), dated 
November 14, 2012, which is not incorporated by reference in this 
AD: The actions specified in paragraph (g)(2) of this AD are not 
required for the rigid fuel couplings only. However, the actions 
specified in paragraph (g)(2) of this AD are required for the full 
flexible couplings, even if inspected prior to the effective date of 
this AD as specified in Boeing Multi Operator Message MOM-MOM-12-
0838-01B, dated November 11, 2012, which is not incorporated by 
reference in this AD; or Boeing Multi Operator Message MOM-MOM-12-
0838-01B(R1), dated November 14, 2012, which is not incorporated by 
reference in this AD.

(i) No Reporting Requirement

    Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2), including 
Attachment A, dated November 25, 2012, specifies reporting to Boeing 
any anomalies found during inspection of the assembly of the rigid 
and full flexible couplings, including anomalies of the lockwire 
installation. This AD does not require any report.

(j) Special Flight Permit

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be modified, provided the lockwire is correctly installed on the 
engine fuel feed manifold rigid and full flexible couplings in 
accordance with paragraph (g)(1) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
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 manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) 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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Sherry Vevea, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6514; fax: 425-917-6590; email: 
sherry.vevea@faa.gov.

[[Page 72203]]

    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced 
service information 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.

(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.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2), 
including Attachment A, dated November 25, 2012. The document number 
and issue date are identified on page 1 of Boeing Multi Operator 
Message MOM-MOM-12-0838-01B(R2), including Attachment A, dated 
November 25, 2012, and on each page of Attachment A; no other page 
of this document contains this information.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at 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.
    (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 https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 28, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-29405 Filed 12-4-12; 8:45 am]
BILLING CODE 4910-13-P
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