Airworthiness Directives; General Electric Company GE90-110B1, GE90-113B, and GE90-115B Series Turbofan Engines, 66042-66045 [E9-29428]

Download as PDF 66042 Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations Actions Compliance Procedures (2) Inspect and repair as necessary the anti-ice fluid line compression fittings. Accomplishment of all of the actions specified in Cirrus SR22 service bulletin SB 2X–30–08, dated November 9, 2009, terminates the placard requirements specified in paragraph (f)(1) of this AD. (i) Inspect at the next scheduled inspection after December 21, 2009 (the effective date of this AD) or within the next 100 hours time-in-service after December 21, 2009 (the effective date of this AD), whichever occurs first. (ii) Repair before further flight after the inspection specified in paragraph (f)(2) of this AD where any incorrectly installed compression fittings are found. Follow Cirrus SR22 Service Bulletin SB 2X– 30–08, dated November 9, 2009. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (g) The Manager, Chicago 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. Send information to ATTN: Anthony Flores, Aerospace Engineer, Chicago Aircraft Certification Office (ACO), 2300 E. Devon Ave., Room 107, Des Plaines, Illinois 60018; telephone: (847) 294–7140; fax: (847) 294–7834. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Federal Aviation Administration Material Incorporated by Reference srobinson on DSKHWCL6B1PROD with RULES (h) You must use Cirrus SR22 Service Bulletin SB 2X–30–08, dated November 9, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, MN 55811–1548; telephone: (218) 788–3000; fax: (218) 788– 3525; e-mail: fieldservice@cirrusaircraft.com; Internet: https://cirrusaircraft.com. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Kansas City, Missouri, on December 4, 2009. William Timberlake, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–29578 Filed 12–11–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 16:24 Dec 11, 2009 Jkt 220001 14 CFR Part 39 [Docket No. FAA–2009–0018; Directorate Identifier 2009–NE–01–AD; Amendment 39– 16044; AD 2009–21–07] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF6–80C2 Series Turbofan Engines; Correction AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; correction. SUMMARY: The FAA is correcting airworthiness directive (AD) 2009–21– 07, which published in the Federal Register. That AD applies to General Electric Company (GE) CF6–80C2 series turbofan engines with certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators installed. The unsafe condition statement of ‘‘We are issuing this AD to prevent loss of asymmetric thrust and thrust control’’, and rod-end part number ‘‘MS2124S06’’ in paragraph (j) are incorrect. This document corrects the unsafe condition statement and the part number. In all other respects, the original document remains the same. DATES: Effective December 14, 2009. FOR FURTHER INFORMATION CONTACT: Christopher J. Richards, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.j.richards@faa.gov; telephone (781) 238–7133; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: On October 27, 2009 (74 FR 55126), we published a final rule AD, FR Doc. E9– 24391, in the Federal Register. That AD applies to GE CF6–80C2 series turbofan engines with certain thrust reverser ballscrew gearbox assembly adjustablelength end actuators installed. We need to make the following corrections: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 § 39.13 [Corrected] On page 55126, in the second column, in the last sentence of the Summary Section, ‘‘We are issuing this AD to prevent loss of asymmetric thrust and thrust control.’’ is corrected to read ‘‘We are issuing this AD to prevent asymmetric thrust and loss of thrust control.’’ On page 55129, in the third column, in the last sentence of paragraph (d), ‘‘We are issuing this AD to prevent loss of asymmetric thrust and thrust control.’’ is corrected to read ‘‘We are issuing this AD to prevent asymmetric thrust and loss of thrust control.’’ On page 55130, in the first column, in paragraph (j), in the third line, ‘‘MS2124S06’’ is corrected to read ‘‘MS21242S06.’’ Issued in Burlington, Massachusetts, on December 4, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–29483 Filed 12–11–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0143; Directorate Identifier 2009–NE–05–AD; Amendment 39– 16135; AD 2009–25–14] RIN 2120–AA64 Airworthiness Directives; General Electric Company GE90–110B1, GE90– 113B, and GE90–115B Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) GE90–110B1, GE90–113B, and GE90–115B series turbofan engines with stage 6 lowpressure turbine (LPT) blades, part number (P/N) 1765M37P03 or P/N E:\FR\FM\14DER1.SGM 14DER1 srobinson on DSKHWCL6B1PROD with RULES Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations 1765M37P04, installed. This AD requires initial and repetitive inspections for shroud interlock wear of the stage 6 LPT blades. This AD also requires replacing those blades with stage 6 LPT blades eligible for installation at the next engine shop visit as terminating action to the repetitive blade inspections. This AD results from eight reports of GE90–115B stage 6 LPT single-blade separation events. We are issuing this AD to prevent failure of stage 6 LPT blades, which could result in uncontained engine failure and damage to the airplane. DATES: This AD becomes effective January 19, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 19, 2010. ADDRESSES: You can get the service information identified in this AD from General Electric Company via GE– Aviation, Attn: Distributions, 111 Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552–3272; fax (513) 552–3329. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: barbara.caufield@faa.gov; telephone (781) 238–7146; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE GE90–110B1, GE90–113B, and GE90–115B series turbofan engines with stage 6 LPT blades, P/N 1765M37P03 or P/N 1765M37P04, installed. We published the proposed AD in the Federal Register on June 24, 2009 (74 FR 30020). That action proposed to require initial and repetitive inspections for shroud interlock wear of the stage 6 LPT blades. That action also proposed to require replacing those blades with stage 6 LPT blades eligible for installation at the next engine shop visit as terminating action to the repetitive blade inspections. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, VerDate Nov<24>2008 16:24 Dec 11, 2009 Jkt 220001 66043 except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Request To Reference the Latest GE SB Revision GE Aviation, Japan Airlines, and Eva Air request that we reference using latest GE SB in the AD, which is SB No. GE90–100 SB 72–0260, Revision 7, dated June 2, 2009. We agree and have referenced the use of Revision 7 in the AD. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Reference the Use of LaterFAA-Approved SB Revisions One commenter, V Australia, requests that we state to use ‘‘or later-FAAapproved revision of the SB’’ in the AD. The commenter states that Revision 7 has been issued since the proposed AD was issued, and it is likely that GE will issue more revisions. We do not agree. Rulemaking requirements do not permit advance approval of unknown future revisions to service bulletins. We did not change the AD. Request To Include Service Bulletin (SB) Revision 3 One commenter, All Nippon Airways, requests that we include GE SB No. GE90–100 SB 72–0260, Revision 3, dated July 17, 2008, in Previous Credit paragraph (i). We do not agree. That SB does not specifically call out the need to inspect engines with replacement, original configuration, stage 6 LPT blades. We did not change the AD. Request To Correct SB Paragraph References All Nippon Airways and Japan Airlines requests that in paragraph (f), we correct the reference of what paragraphs to use in the SB, from ‘‘3.A through 3.A.(3)(g)(12)’’, to ‘‘3.A through 3.A.(2)(g)(12)’’. We agree the reference needs correcting. We made the correction, but listed the latest revision of the SB, which is GE SB No. GE90–100 SB 72– 0260, Revision 7, dated June 2, 2009. We also added SB No. GE90–100 SB 72– 0260, Revision 6, dated May 1, 2009, to the Previous Credit paragraph. Requests To Change the Unsafe Condition Paragraph (d) GE Aviation requests that we change the Unsafe Condition paragraph (d) to state that, in each case, the engine continued to produce commanded thrust. We do not agree. Although the statement is true, adding it would lessen the impact of, and detract from, the existing unsafe condition statement. We did not change the AD. Boeing requests that we change the Unsafe Condition paragraph (d) to also state that there is a remote possibility of the unsafe condition event occurring on both engines on a given flight. We do not agree. We considered the possibility of a dual-engine failure event during our safety analysis and when determining the appropriate compliance actions for this AD. We did not change the AD. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Request To Add SB Revision 6 to Previous Credit Paragraph (i) GE Aviation and Japan Airlines request that we add GE SB No. GE90– 100 SB 72–0260, Revision 6, dated May 1, 2009, to the list of SB revisions in the Previous Credit paragraph (i). We agree and added SB Revision 6 to that paragraph. Request for Change in Definition Paragraph (j) Japan Airlines requests that we change the Definition paragraph (j) to exclude the induction of engines into the shop for maintenance action that can be performed at line maintenance, but which is performed in the shop for operator convenience. The commenter states that making this change will help eliminate an unnecessary burden to the operators. We do not agree. The existing engine shop visit definition is intended to lead operators to perform the terminating action as soon as possible. Doing this will reduce the reliance upon repetitive inspections and continued risk of blade failure. We did not change the AD. Conclusion We have carefully 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. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect four GE GE90–110B1, GE90–113B, and E:\FR\FM\14DER1.SGM 14DER1 66044 Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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. srobinson on DSKHWCL6B1PROD with RULES GE90–115B series engines installed on airplanes of U.S. registry. We also estimate that it will take about 18 workhours per engine to perform one inspection of the stage 6 LPT blades, and that the average labor rate is $80 per work-hour. Replacement stage 6 LPT blades will cost $258,280 per engine. We estimate that no additional labor costs will be incurred to perform the required blade replacements, because the replacements will be done during a scheduled engine shop visit. Based on these figures, we estimate the total cost of the AD for one inspection to U.S. operators to be $1,038,880. Authority: 49 U.S.C. 106(g), 40113, 44701. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. VerDate Nov<24>2008 16:24 Dec 11, 2009 Jkt 220001 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2009–25–14 General Electric Company: Amendment 39–16135. Docket No. FAA–2009–0143; Directorate Identifier 2009–NE–05–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 19, 2010. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) GE90–110B1, GE90–113B, and GE90–115B series turbofan engines with stage 6 low-pressure turbine (LPT) blades, part number (P/N) 1765M37P03 or P/N 1765M37P04, installed. These engines are installed on, but not limited to, Boeing 777– 200LR, 777–300ER, and 777 Freighter series airplanes. Unsafe Condition (d) This AD results from eight reports of GE90–115B stage 6 LPT single-blade separation events. We are issuing this AD to prevent failure of stage 6 LPT blades, which could result in uncontained engine failure and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections (f) Before accumulating 3,000 engine operating hours time-since-new, or 400 engine cycles-since-new, whichever occurs first, inspect the stage 6 LPT blades, P/N 1765M37P03 or P/N 1765M37P04 for shroud interlock wear. Thereafter, re-inspect within every 1,000 engine operating hours, or within 125 engine cycles-since-last inspection, whichever occurs first. Use paragraphs 3.A. through 3.A.(2)(g)(12) of the Accomplishment Instructions of GE Service Bulletin (SB) No. GE90–100 SB 72–0260, Revision 7, dated June 2, 2009, to do both the initial and repetitive inspections. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Terminating Action (g) At the next engine shop visit, replace the stage 6 LPT blades, P/N 1765M37P03 or P/N 1765M37P04, with stage 6 LPT blades eligible for installation as terminating action to the repetitive inspections required by this AD. Installation Prohibition of Affected Stage 6 LPT Blades (h) After the effective date of this AD, do not install any stage 6 LPT blades, P/N 1765M37P03 or P/N 1765M37P04, onto any engine. Previous Credit (i) An inspection performed before the effective date of this AD using GE SB No. GE90–100 SB 72–0260, Revision 4, dated October 8, 2008, or Revision 5, dated November 7, 2008, or Revision 6, dated May 1, 2009, satisfies the initial inspection requirement of this AD. Definition (j) For the purpose of this AD, an engine shop visit is induction of the engine into the shop for any cause. Alternative Methods of Compliance (k) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (l) Contact Barbara Caufield, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: barbara.caufield@faa.gov; telephone (781) 238–7146; fax (781) 238– 7199, for more information about this AD. (m) Guidance on determining which stage 6 LPT blades are eligible for installation can be found in GE Service Bulletin No. 72–0279, Revision 1, dated December 11, 2008, and GE Service Bulletin No. 72–0313, dated March 18, 2009. Material Incorporated by Reference (n) You must use GE Service Bulletin No. GE90–100 SB 72–0260, Revision 7, dated June 2, 2009, to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General Electric Company via GE–Aviation, Attn: Distributions, 111 Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552–3272; fax (513) 552–3329, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. E:\FR\FM\14DER1.SGM 14DER1 Federal Register / Vol. 74, No. 238 / Monday, December 14, 2009 / Rules and Regulations Issued in Burlington, Massachusetts, on December 4, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–29428 Filed 12–11–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1124; Directorate Identifier 2009–SW–35–AD; Amendment 39– 16128; AD 2009–25–09] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model SA 330 F, G, and J Helicopters AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. We are adopting a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI Emergency AD states that there has been a report of the failure of a flexible coupling on one of the main gearbox (MGB) inputs, which may be the result of loss of the tightening torque load, or insufficient tightening of the nuts on the bolts fixing the discs of the flexible coupling to its sliding and fixed hinges. This condition, if not corrected, could result in failure of the coupling discs, and if this condition develops on both the left-hand (LH) and right-hand (RH) MGB inputs, a complete loss of power to the transmission and subsequent loss of control of the helicopter. DATES: This AD becomes effective on December 29, 2009. The incorporation by reference of certain publications is approved by the Director of the Federal Register as of December 29, 2009. We must receive comments on this AD by February 12, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting your comments electronically. srobinson on DSKHWCL6B1PROD with RULES SUMMARY: VerDate Nov<24>2008 16:24 Dec 11, 2009 Jkt 220001 • 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. You may get the service information identified in this AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at https:// www.eurocopter.com. Examining the Docket: You may examine the AD docket on the Internet at https://www.regulations.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is stated in the ADDRESSES section of this AD. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Ed Cuevas, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone 817–222– 5355, fax 817–222–5961. SUPPLEMENTARY INFORMATION: Discussion The EASA, which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2008–0049–E, dated March 3, 2008 (Corrected: March 7, 2008), to correct an unsafe condition for Eurocopter Model SA 330 F, G, and J helicopters, all serial numbers, with MGB input flexible coupling sliding and fixed flanges assemblies installed that have been modified per MOD 0752416 and MOD 0752419, but have not been subject to maintenance scheduled inspection per Working Card 65.32.601 since new or since a complete overhaul of the MGB. There has been one report of the failure of a modified flexible coupling assembly on one of the MGB inputs, which EASA has deemed to be the result of the loss of the tightening torque load, or insufficient tightening of the nuts on the bolts attaching the disks of the flexible coupling to its sliding and fixed flanges. This condition, if not PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 66045 corrected, could result in progressive fatigue failure of the coupling discs, caused by extensive fretting on the faces and in the holes of the flexible coupling discs. If this unsafe condition develops on both the LH and RH MGB inputs, it could result in a complete loss of power to the transmission and subsequent loss of control of the helicopter. Related Service Information Eurocopter has issued Emergency Alert Service Bulletin No. 05.95, dated March 3, 2008, which specifies readjusting or checking the tightening torque load of the nuts on the bolts attaching the flexible coupling to the sliding coupling flange and the bolts attaching the flexible coupling to the fixed coupling flange, in order to prevent any damage to the flexible couplings, which, over time, may lead to the loss of input drive to the MGB. The actions described in the MCAI are intended to correct the same unsafe conditions as those identified in the service information. FAA’s Evaluation and Unsafe Condition Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, their Technical Agent, has notified us of the unsafe condition described in the MCAI AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe conditions exist and are likely to exist or develop on other helicopters of these same type designs. Differences Between This AD and the MCAI AD The MCAI AD uses the term ‘‘flight hours’’ instead of ‘‘hours time-inservice’’, as we have used in this AD. Also, the MCAI AD allows ‘‘use of later approved revisions’’ of the service information to comply with the MCAI AD. Our AD requires compliance in accordance with the Eurocopter EASB. Additionally, this AD requires ‘‘inspections’’ conducted by a qualified mechanic, instead of ‘‘checks’’, which we allow a pilot to do. Finally, contacting Eurocopter Technical Support is not required by this AD as it is by the MCAI AD. Costs of Compliance We estimate that this AD will affect about 14 helicopters of U.S. registry. We also estimate that it will take about: • 8 work-hours per helicopter to remove the engine, re-adjust the E:\FR\FM\14DER1.SGM 14DER1

Agencies

[Federal Register Volume 74, Number 238 (Monday, December 14, 2009)]
[Rules and Regulations]
[Pages 66042-66045]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29428]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0143; Directorate Identifier 2009-NE-05-AD; 
Amendment 39-16135; AD 2009-25-14]
RIN 2120-AA64


Airworthiness Directives; General Electric Company GE90-110B1, 
GE90-113B, and GE90-115B Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
General Electric Company (GE) GE90-110B1, GE90-113B, and GE90-115B 
series turbofan engines with stage 6 low-pressure turbine (LPT) blades, 
part number (P/N) 1765M37P03 or P/N

[[Page 66043]]

1765M37P04, installed. This AD requires initial and repetitive 
inspections for shroud interlock wear of the stage 6 LPT blades. This 
AD also requires replacing those blades with stage 6 LPT blades 
eligible for installation at the next engine shop visit as terminating 
action to the repetitive blade inspections. This AD results from eight 
reports of GE90-115B stage 6 LPT single-blade separation events. We are 
issuing this AD to prevent failure of stage 6 LPT blades, which could 
result in uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective January 19, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of January 19, 2010.

ADDRESSES: You can get the service information identified in this AD 
from General Electric Company via GE-Aviation, Attn: Distributions, 111 
Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552-
3272; fax (513) 552-3329.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
barbara.caufield@faa.gov; telephone (781) 238-7146; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE GE90-110B1, GE90-
113B, and GE90-115B series turbofan engines with stage 6 LPT blades, P/
N 1765M37P03 or P/N 1765M37P04, installed. We published the proposed AD 
in the Federal Register on June 24, 2009 (74 FR 30020). That action 
proposed to require initial and repetitive inspections for shroud 
interlock wear of the stage 6 LPT blades. That action also proposed to 
require replacing those blades with stage 6 LPT blades eligible for 
installation at the next engine shop visit as terminating action to the 
repetitive blade inspections.

Examining the AD Docket

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

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Include Service Bulletin (SB) Revision 3

    One commenter, All Nippon Airways, requests that we include GE SB 
No. GE90-100 SB 72-0260, Revision 3, dated July 17, 2008, in Previous 
Credit paragraph (i).
    We do not agree. That SB does not specifically call out the need to 
inspect engines with replacement, original configuration, stage 6 LPT 
blades. We did not change the AD.

Request To Correct SB Paragraph References

    All Nippon Airways and Japan Airlines requests that in paragraph 
(f), we correct the reference of what paragraphs to use in the SB, from 
``3.A through 3.A.(3)(g)(12)'', to ``3.A through 3.A.(2)(g)(12)''.
    We agree the reference needs correcting. We made the correction, 
but listed the latest revision of the SB, which is GE SB No. GE90-100 
SB 72-0260, Revision 7, dated June 2, 2009. We also added SB No. GE90-
100 SB 72-0260, Revision 6, dated May 1, 2009, to the Previous Credit 
paragraph.

Requests To Change the Unsafe Condition Paragraph (d)

    GE Aviation requests that we change the Unsafe Condition paragraph 
(d) to state that, in each case, the engine continued to produce 
commanded thrust.
    We do not agree. Although the statement is true, adding it would 
lessen the impact of, and detract from, the existing unsafe condition 
statement. We did not change the AD.
    Boeing requests that we change the Unsafe Condition paragraph (d) 
to also state that there is a remote possibility of the unsafe 
condition event occurring on both engines on a given flight.
    We do not agree. We considered the possibility of a dual-engine 
failure event during our safety analysis and when determining the 
appropriate compliance actions for this AD. We did not change the AD.

Request To Reference the Latest GE SB Revision

    GE Aviation, Japan Airlines, and Eva Air request that we reference 
using latest GE SB in the AD, which is SB No. GE90-100 SB 72-0260, 
Revision 7, dated June 2, 2009.
    We agree and have referenced the use of Revision 7 in the AD.

Request To Reference the Use of Later-FAA-Approved SB Revisions

    One commenter, V Australia, requests that we state to use ``or 
later-FAA-approved revision of the SB'' in the AD. The commenter states 
that Revision 7 has been issued since the proposed AD was issued, and 
it is likely that GE will issue more revisions.
    We do not agree. Rulemaking requirements do not permit advance 
approval of unknown future revisions to service bulletins. We did not 
change the AD.

Request To Add SB Revision 6 to Previous Credit Paragraph (i)

    GE Aviation and Japan Airlines request that we add GE SB No. GE90-
100 SB 72-0260, Revision 6, dated May 1, 2009, to the list of SB 
revisions in the Previous Credit paragraph (i).
    We agree and added SB Revision 6 to that paragraph.

Request for Change in Definition Paragraph (j)

    Japan Airlines requests that we change the Definition paragraph (j) 
to exclude the induction of engines into the shop for maintenance 
action that can be performed at line maintenance, but which is 
performed in the shop for operator convenience. The commenter states 
that making this change will help eliminate an unnecessary burden to 
the operators.
    We do not agree. The existing engine shop visit definition is 
intended to lead operators to perform the terminating action as soon as 
possible. Doing this will reduce the reliance upon repetitive 
inspections and continued risk of blade failure. We did not change the 
AD.

Conclusion

    We have carefully 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. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect four GE GE90-110B1, GE90-113B, 
and

[[Page 66044]]

GE90-115B series engines installed on airplanes of U.S. registry. We 
also estimate that it will take about 18 work-hours per engine to 
perform one inspection of the stage 6 LPT blades, and that the average 
labor rate is $80 per work-hour. Replacement stage 6 LPT blades will 
cost $258,280 per engine. We estimate that no additional labor costs 
will be incurred to perform the required blade replacements, because 
the replacements will be done during a scheduled engine shop visit. 
Based on these figures, we estimate the total cost of the AD for one 
inspection to U.S. operators to be $1,038,880.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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:

2009-25-14 General Electric Company: Amendment 39-16135. Docket No. 
FAA-2009-0143; Directorate Identifier 2009-NE-05-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
19, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) GE90-110B1, 
GE90-113B, and GE90-115B series turbofan engines with stage 6 low-
pressure turbine (LPT) blades, part number (P/N) 1765M37P03 or P/N 
1765M37P04, installed. These engines are installed on, but not 
limited to, Boeing 777-200LR, 777-300ER, and 777 Freighter series 
airplanes.

Unsafe Condition

    (d) This AD results from eight reports of GE90-115B stage 6 LPT 
single-blade separation events. We are issuing this AD to prevent 
failure of stage 6 LPT blades, which could result in uncontained 
engine failure and damage to the airplane.

Compliance

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

Inspections

    (f) Before accumulating 3,000 engine operating hours time-since-
new, or 400 engine cycles-since-new, whichever occurs first, inspect 
the stage 6 LPT blades, P/N 1765M37P03 or P/N 1765M37P04 for shroud 
interlock wear. Thereafter, re-inspect within every 1,000 engine 
operating hours, or within 125 engine cycles-since-last inspection, 
whichever occurs first. Use paragraphs 3.A. through 3.A.(2)(g)(12) 
of the Accomplishment Instructions of GE Service Bulletin (SB) No. 
GE90-100 SB 72-0260, Revision 7, dated June 2, 2009, to do both the 
initial and repetitive inspections.

Terminating Action

    (g) At the next engine shop visit, replace the stage 6 LPT 
blades, P/N 1765M37P03 or P/N 1765M37P04, with stage 6 LPT blades 
eligible for installation as terminating action to the repetitive 
inspections required by this AD.

Installation Prohibition of Affected Stage 6 LPT Blades

    (h) After the effective date of this AD, do not install any 
stage 6 LPT blades, P/N 1765M37P03 or P/N 1765M37P04, onto any 
engine.

Previous Credit

    (i) An inspection performed before the effective date of this AD 
using GE SB No. GE90-100 SB 72-0260, Revision 4, dated October 8, 
2008, or Revision 5, dated November 7, 2008, or Revision 6, dated 
May 1, 2009, satisfies the initial inspection requirement of this 
AD.

Definition

    (j) For the purpose of this AD, an engine shop visit is 
induction of the engine into the shop for any cause.

Alternative Methods of Compliance

    (k) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD, if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (l) Contact Barbara Caufield, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
barbara.caufield@faa.gov; telephone (781) 238-7146; fax (781) 238-
7199, for more information about this AD.
    (m) Guidance on determining which stage 6 LPT blades are 
eligible for installation can be found in GE Service Bulletin No. 
72-0279, Revision 1, dated December 11, 2008, and GE Service 
Bulletin No. 72-0313, dated March 18, 2009.

Material Incorporated by Reference

    (n) You must use GE Service Bulletin No. GE90-100 SB 72-0260, 
Revision 7, dated June 2, 2009, to perform the inspections required 
by this AD. The Director of the Federal Register approved the 
incorporation by reference of this service bulletin in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General Electric 
Company via GE-Aviation, Attn: Distributions, 111 Merchant St., Room 
230, Cincinnati, Ohio 45246; telephone (513) 552-3272; fax (513) 
552-3329, for a copy of this service information. You may review 
copies at the FAA, New England Region, 12 New England Executive 
Park, Burlington, MA; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


[[Page 66045]]


    Issued in Burlington, Massachusetts, on December 4, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-29428 Filed 12-11-09; 8:45 am]
BILLING CODE 4910-13-P
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