[Federal Register: October 23, 2008 (Volume 73, Number 206)] [Proposed Rules] [Page 63090-63094] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr23oc08-18] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2008-0952; Directorate Identifier 98-ANE-49-AD] RIN 2120-AA64 Airworthiness Directives; General Electric Company CF6-80A, CF6- 80C2, and CF6-80E1 Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for General Electric Company (GE) CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines. That AD currently requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required inspection of selected critical life-limited parts at each piece-part exposure. This proposed AD would require revisions to the CF6-80A, CF6- 80C2, and CF6-80E1 series engines ALS sections of the manufacturer's manuals and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements, and to update certain Engine Manual Inspection Task and Sub Task Number references. This proposed AD results from the need to require enhanced inspection of selected critical life-limited parts of CF6-80A, CF6- 80C2, and CF6-80E1 series engines. We are proposing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane. DATES: We must receive any comments on this proposed AD by December 22, 2008. ADDRESSES: Use one of the following addresses to comment on this proposed AD. Federal eRulemaking Portal: Go to http:// www.regulations.gov and follow the instructions for sending your comments electronically. Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Fax: (202) 493-2251. FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone (781) 238-7754; (781) 238-7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ``Docket No. FAA-2008-0952; Directorate Identifier 98-ANE-49-AD'' in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78). 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 this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion On April 3, 2002, we issued AD 2002-07-12, Amendment 39-12707 (67 FR 17279, April 10, 2002), to require revisions to the ALS of the manufacturer's ICA for GE CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. Additional Inspection Procedures Since the issuance of that AD, an FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for additional mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained engine failures. This proposal would require revisions to the CF6-80A, CF6-80C2, and CF6-80E1 series engines ALS sections of the manufacturer's manuals and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. FAA's Determination and Requirements of the Proposed AD Since an unsafe condition has been identified that is likely to exist or develop on other products of this same type design, the proposed AD would supersede AD 2002-07-12 to add additional inspections for certain high-pressure turbine (HPT) components, and to update certain Engine Manual Inspection Task and or Sub Task Number references. These inspections would be required at each piece-part opportunity. For reference, this proposed AD carries forward the requirements from AD 2002-07-12. Also for reference, the parts added to the table in the compliance section of this AD are identified by an asterisk (*) that precedes the part nomenclature. Also for reference, parts that have an Engine Manual Inspection Task and or Sub Task Number reference updated in the table in the compliance section of this AD, are identified by two asterisks (**) that precede the part nomenclature. Costs of Compliance We estimate that this proposed AD would affect 315 CF6-80A series engines and 926 CF6-80C2 series engines installed on airplanes of U.S. [[Page 63091]] registry. We also estimate that it would take about 5 work-hours per CF6-80A series engine and about 2 work-hours per CF6-80C2 series engine to do the proposed additional inspections and that the average labor rate is $80 per work-hour. The total cost of the new inspections per CF6-80A series engine would be about $400. The total cost of the new inspections per CF6-80C2 series engine would be about $160. We estimate that there will be about 42 shop visits per year for CF6-80A series engines, and about 128 shop visits per year for CF6-80C2 series engines that result in piece-part-exposure of the added affected components. Therefore, we estimate the total annual cost for the additional inspections to be $37,280. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Would 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 proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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. Sec. 39.13 [Amended] 2. The FAA amends Sec. 39.13 by removing Amendment 39-12707 (67 FR 17279, April 10, 2002) and by adding a new airworthiness directive to read as follows: General Electric Company: Docket No. FAA-2008-0952; Directorate Identifier 98-ANE-49-AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by December 22, 2008. Affected ADs (b) This AD supersedes AD 2002-07-12, Amendment 39-12707. Applicability (c) This AD applies to General Electric Company CF6-80A, CF6- 80C2, and CF6-80E1 series turbofan engines. These engines are installed on, but not limited to, Airbus A300, A310, and A330 series, Boeing 747 and 767 series, and McDonnell Douglas MD-11 series airplanes. Unsafe Condition (d) This AD results from the need to require enhanced inspection of selected critical life-limited parts of CF6-80A, CF6-80C2, and CF6-80E1 series engines. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an 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) Within the next 180 days after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA), and for air carrier operations revise the approved continuous airworthiness maintenance program, by adding the following: ``MANDATORY INSPECTIONS (1) Perform inspections of the following parts at each piece- part opportunity in accordance with the instructions provided in the applicable manual provisions: ------------------------------------------------------------------------ Inspect per engine Part nomenclature Part No. (P/N) manual inspection chapter ------------------------------------------------------------------------ For CF6-80A Engines ------------------------------------------------------------------------ Disk, Fan Rotor, Stage 1...... All.............. 72-21-03 Paragraph 3. Fluorescent- Penetrant Inspect, and 72-21-03 Paragraph 4. Eddy Current Inspect. Fan Forward Shaft............. All.............. 72-21-05 Paragraph 2. Magnetic Particle Inspect. Fan Mid Shaft................. All.............. 72-24-01 Paragraph 2. Magnetic Particle Inspect. Disk, HPC Rotor, Stage One.... All.............. 72-31-04 Paragraph 3. Fluorescent- Penetrant Inspect. ** Disk, HPC Rotor, Stage Two. All.............. 72-31-05 Paragraph 4. Fluorescent- Penetrant Inspect. Spool, HPC Rotor, Stage 3-9... All.............. 72-31-06 Paragraph 3. Fluorescent- Penetrant Inspect. Disk, HPC Rotor, Stage 10..... All.............. 72-31-07 Paragraph 3. Fluorescent- Penetrant Inspect. Spool, HPC Rotor, Stage 11-14. All.............. 72-31-08 Paragraph 3.A. Fluorescent- Penetrant Inspect. Rotating CDP Seal............. All.............. 72-31-10 Paragraph 3. Fluorescent- Penetrant Inspect. Disk Shaft, HPT Rotor Stage All.............. 72-53-02 Paragraph 3. One. Fluorescent- Penetrant Inspect per 70-32-02, and 72-53-02 Paragraph 6.C. Disk Rim Bolt Hole Eddy Current Inspection, and 72-53-02 Paragraph 6.D. Disk Bore Eddy Current Inspection. * Disk Shaft, HPT Rotor Stage All.............. 72-53-02 Paragraph One. 6.E. Disk Dovetail Slot Bottom Eddy Current Inspection. [[Page 63092]] * Disk Shaft, HPT Rotor, Stage P/Ns 2047M33G01 72-53-02 Paragraph 7. One. thru G10, and P/ Disk Dovetail Slot N 9362M58G11. Bottom Aft Corner Chamfers Eddy Current Inspection. Disk, HPT Rotor, Stage Two.... All.............. 72-53-06 Paragraph 3. Fluorescent- Penetrant Inspection, and 72-53-06 Paragraph 6. Eddy Current Inspection of Rim Bolt Holes for Cracks, and 72-53-06 Paragraph 7. Disk Bore Eddy Current Inspection. Disk, LPT Rotor Stage 1-4..... All.............. 72-57-02 Paragraph 3. Fluorescent- Penetrant Inspection. Shaft, LPT Rotor.............. All.............. 72-57-03 Paragraph 3. Fluorescent- Penetrant Inspection, and 72-57-03 Paragraph 6. Eddy Current Inspection. ------------------------------------------------------------------------ For All CF6-80C2 Engines ------------------------------------------------------------------------ Disk, Fan Rotor, Stage 1...... All.............. Task 72-21-03-200-000- 004 Fluorescent- Penetrant Inspection, and Task 72-21-03-200-000- 008 Eddy Current Inspect Fan Rotor Disk Stage 1 Bore, Forward and Aft Hub Faces, and Bore Radii. Shaft, Fan Forward............ All.............. Task 72-21-05-200-000- 001 Fluorescent Penetrant Inspection, and Task 72-21-05-200-000- 005 Vent Hole Eddy Current Inspection. Fan Mid Shaft................. All.............. Task 72-24-01-200-000- 003 Magnetic Particle Inspection. HPCR Stage 1 Disk............. All.............. Task 72-31-04-200-000- 002 Fluorescent Penetrant Inspection. HPCR Stage 2 Disk............. All.............. Task 72-31-05-200-000- 002 Fluorescent Penetrant Inspection. HPCR Stage 3-9 Spool.......... All.............. Task 72-31-06-200-000- 001 Fluorescent Penetrant Inspection. HPCR Stage 10 Disk............ All.............. Task 72-31-07-200-000- 001 Fluorescent Penetrant Inspection. HPCR Stage 11-14 Spool/Shaft.. All.............. Task 72-31-08-200-000- 002 Fluorescent Penetrant Inspection. No. 4 Bearing Rotating (CDP) All.............. Task 72-31-10-200-000- Air Seal. 001 Fluorescent Penetrant Inspection or Task 72-31-10-200-000- A01 Fluorescent Penetrant Inspection. HPCR Stage 10-14 Spool/Shaft.. All.............. Task 72-31-22-200-000- 002 Fluorescent Penetrant Inspection. ** Disk/Shaft, HPT Rotor, All.............. Task 72-53-02-200-000- Stage One. 001 (Inspection-- Configuration 1), or Task 72-53-02-230- 801 (Inspection-- Configuration 2), Fluorescent- Penetrant Inspect, and Task 72-53-02-200-000- 005 (Inspection-- Configuration 1), or Task 72-53-02-250- 802 (Inspection-- Configuration 2), Disk Rim Bolt Hole Eddy Current Inspection, and Task 72-53-02-200-000- 006 (Inspection-- Configuration 1), or Task 72-53-02-250- 803 (Inspection-- Configuration 2), Disk Bore Area Eddy Current Inspection, and Task 72-53-02-200-000- 007 (Inspection-- Configuration 1), or Task 72-53-02-250- 804 (Inspection-- Configuration 2), Disk Dovetail Slot Bottom Eddy Current. * Disk/Shaft, HPT Rotor, Stage P/N 1531M84G12 Task 72-53-02-250-801 One. and P/Ns (Inspection--Configu 2047M32G01 thru ration 1), Disk G07. Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection. Disk, HPT Rotor, Stage Two.... All.............. Task 72-53-06-200-000- 002 Fluorescent- Penetrant Inspect, and Task 72-53-06-200-000- 006 Disk Rim Bolt Hole Eddy Current Inspection, and Task 72-53-06-200-000- 007 Disk Bore Eddy Current Inspection. LPTR Stage 1-5 Disks.......... All.............. Task 72-57-02-200-000- 001 Fluorescent- Penetrant Inspection. LPTR Shaft.................... All.............. Task 72-57-03-200-000- 002 Fluorescent- Penetrant Inspect, and Task 72-57-03-200-000- 006 Eddy Current Inspection. ------------------------------------------------------------------------ For CF6-80C2 Engines configured with the R88DT Turbine (Models CF6- 80C2B2F, 80C2B4F, 80C2B6F, 80C2B7F, 80C2B8F) ------------------------------------------------------------------------ Disk/Shaft, HPT Rotor, Stage All.............. Task 72-53-16-200-000- One (R88DT, No Rim Bolt 001 Fluorescent- Holes). Penetrant Inspect, and Task 72-53-16-200-000- 005 Disk Bore Area Eddy Current Inspection. Disk, HPT Rotor, Stage Two All.............. Task 72-53-18-200-000- (R88DT, No Rim Bolt Holes). 002 Fluorescent- Penetrant Inspect, and Task 72-53-18-200-000- 005 Disk Bore Area Eddy Current Inspection. Rotating Interstage Seal All.............. Task 72-53-17-200-000- (R88DT). 001 Fluorescent- Penetrant Inspect, and Task 72-53-17-200-000- 005 Seal Bore Area Eddy Current. Forward Outer Seal (R88DT).... All.............. Task 72-53-21-200-000- 001 Fluorescent- Penetrant Inspect, and Task 72-53-21-200-000- 004 Seal Bore Area Eddy Current. ------------------------------------------------------------------------ For CF6-80E1 Engines ------------------------------------------------------------------------ Disk, Fan Rotor, Stage One.... All.............. Sub Task 72-21-03-230- 051 Fluorescent- Penetrant Inspection, and Sub Task 72-21-03-250- 051 or 72-21-03-250- 052 Disk Bore Eddy Current Inspection. Shaft, Fan.................... All.............. Sub Task 72-21-05-230- 051 Fluorescent Penetrant Inspection, and Sub Task 72-21-05-250- 051 Vent Hole Eddy Current Inspection. Compressor Rotor, Stage 1 Disk All.............. Sub Task 72-31-04-230- 051 Fluorescent Penetrant Inspection. Compressor Rotor, Stage 2 Disk All.............. Sub Task 72-31-05-230- 051 Fluorescent Penetrant Inspection. [[Page 63093]] Compressor Rotor, Stage 3-9 All.............. Sub Task 72-31-06-230- Spool. 051 Fluorescent Penetrant Inspection. Compressor Rotor, Stage 10 All.............. Sub Task 72-31-07-230- Disk (Pre SB 72-0150). 051 Fluorescent Penetrant Inspection. Compressor Rotor Spool/Shaft, All.............. Sub Task 72-31-08-230- Stage 11-14 (Pre SB 72-0150). 051 Fluorescent Penetrant Inspection. Compressor Rotor Spool/Shaft, All.............. Sub Task 72-31-23-230- Stage 10-14 (SB 72-0150). 052 Fluorescent Penetrant Inspection. Compressor Rotor No. 4 Bearing All.............. Sub Task 72-31-10-230- Rotating Air Seal (CDP 051 Fluorescent Rotating Seal). Penetrant Inspection. HPT Disk/Shaft, Stage 1....... All.............. Sub Task 72-53-02-230- 051 Fluorescent- Penetrant Inspection, and Sub Task 72-53-02-250- 051 Eddy Current Inspection, Rim Bolt Holes, and Sub Task 72-53-02-250- 054 Eddy Current Inspection, Disk Bore. HPT Disk, Stage 2............. All.............. Sub Task 72-53-06-230- 051 Fluorescent- Penetrant Inspection, and Sub Task 72-53-06-250- 051 Eddy Current Inspection, Rim Bolt Holes, and Sub Task 72-53-06-250- 054 Eddy Current Inspection, Disk Bore. LPT Rotor Shaft............... All.............. Sub Task 72-55-01-240- 051 Magnetic Particle Inspect. LPT Disks, Stages 1-5......... All.............. Sub Task 72-57-02-230- 051 Fluorescent- Penetrant Inspect. LPT Rotor Torque Cone......... All.............. Sub Task 72-57-03-220- 051 Fluorescent- Penetrant Inspect. ------------------------------------------------------------------------ For CF6-80E1 Engines configured with the R88DT Turbine ------------------------------------------------------------------------ Disk/Shaft, HPT Rotor, Stage 1 All.............. Sub Task 72-53-16-230- (R88DT, No Rim Bolt Holes). 052 Fluorescent- Penetrant Inspect, and Sub Task 72-53-16-250- 051 Disk Bore Area Eddy Current Inspection. Disk, HPT Rotor, Stage 2 All.............. Sub Task 72-53-18-230- (R88DT, No Rim Bolt Holes). 051 Fluorescent- Penetrant Inspect, and Sub Task 72-53-18-250- 051 Disk Bore Area Eddy Current Inspection. ** HPT Rotor Rotating All.............. Sub Task 72-53-17-230- Interstage Seal (R88DT). 056 Fluorescent- Penetrant Inspect, and Sub Task 72-53-17-250- 051 Seal Bore Area Eddy Current. HPT Rotor Forward Outer Seal All.............. Sub Task 72-53-21-230- (R88DT). 051 Fluorescent- Penetrant Inspect, and Sub Task 72-53-21-250- 051 Seal Bore Area Eddy Current. ------------------------------------------------------------------------ (2) For the purposes of these mandatory inspections, piece-part opportunity means: (i) The part is considered completely disassembled when accomplished in accordance with the disassembly instructions in the manufacturer's engine manual; and (ii) The part has accumulated more than 100 cycles-in-service since the last piece-part opportunity inspection, provided that the part was not damaged or related to the cause for its removal from the engine. (g) The parts added to the table of this AD are identified by an asterisk (*) that precedes the part nomenclature. Also, parts that have an Engine Manual Inspection Task and/or Sub Task Number reference updated in the table of this AD, are identified by two asterisks (**) that precede the part nomenclature. (h) Except as provided in paragraph (i) of this AD, and notwithstanding contrary provisions in section 43.16 of the Federal Aviation Regulations (14 CFR 43.16), these mandatory inspections shall be performed only in accordance with the ALS of the manufacturer's ICA. Alternative Methods of Compliance (AMOC) (i) You must perform these mandatory inspections using the ALS of the ICA and the applicable Engine Manual unless you receive approval to use an AMOC under paragraph (j) of this AD. Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may not be used to approve alternative methods of compliance or adjustments to the times in which these inspections must be performed. (j) 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. Maintaining Records of the Mandatory Inspections (k) You have met the requirements of this AD when you revise the ALS of the manufacturer's ICA as specified in paragraph (f) of this AD. For air carriers operating under part 121 of the Federal Aviation Regulations (14 CFR part 121), you have met the requirements of this AD when you modify your continuous airworthiness maintenance plan to reflect those changes. You do not need to record each piece-part inspection as compliance to this AD, but you must maintain records of those inspections according to the regulations governing your operation. For air carriers operating under part 121, you may use either the system established to comply with section 121.369 or an alternative accepted by your principal maintenance inspector if that alternative: (1) Includes a method for preserving and retrieving the records of the inspections resulting from this AD; and (2) Meets the requirements of section 121.369(c); and (3) Maintains the records either indefinitely or until the work is repeated. (l) These recordkeeping requirements apply only to the records used to document the mandatory inspections required as a result of revising the ALS of the manufacturer's ICA as specified in paragraph (f) of this AD. These recordkeeping requirements do not alter or amend the recordkeeping requirements for any other AD or regulatory requirement. Related Information (m) Contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199, for more information about this AD. [[Page 63094]] Issued in Burlington, Massachusetts, on October 16, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8-25278 Filed 10-22-08; 8:45 am] BILLING CODE 4910-13-P
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