Airworthiness Directives; General Electric Company CF6-80A, CF6-80C2, and CF6-80E1 Series Turbofan Engines, 7995-7998 [E9-3105]

Download as PDF Federal Register / Vol. 74, No. 34 / Monday, February 23, 2009 / Rules and Regulations rule does not have sufficient federalism implications to warrant the preparation of a federalism summary impact statement. G. Paperwork Reduction Act This final rule does not modify any collection of information as defined in 44 U.S.C. 3502(3), and it will not require a revision to the Form I–9 (OMB Control Number 1615–0047). List of Subjects in 8 CFR Part 274a Administrative practice and procedure, Aliens, Employment, Penalties, Reporting and recordkeeping requirements. Accordingly, part 274a of chapter I of title 8 of the Code of Federal Regulations is amended as follows: ■ PART 274a—CONTROL OF EMPLOYMENT OF ALIENS 1. The authority citation for part 274a continues to read as follows: ■ 2. Section 274a.2 is amended by: a. Adding and reserving paragraph (b)(1)(v)(A)(6), and by ■ b. Adding a new paragraph (b)(1)(v)(A)(7). The additions read as follows: ■ ■ * * * * * (b) * * * (1) * * * (v) * * * (A) * * * (6) [Reserved] (7) In the case of an individual lawfully enlisted for military service in the Armed Forces under 10 U.S.C. 504, a military identification card issued to such individual may be accepted only by the Armed Forces. * * * * * ■ 3. Section 274a.12 is amended by redesignating paragraph (d) as paragraph (e) and adding a new paragraph (d) to read as follows: § 274a.12 Classes of aliens authorized to accept employment. mstockstill on PROD1PC66 with RULES * * * * (d) An alien lawfully enlisted in one of the Armed Forces, or whose enlistment the Secretary with jurisdiction over such Armed Force has determined would be vital to the national interest under 10 U.S.C. 504(b)(2), is authorized to be employed by that Armed Force in military service, if such employment is not otherwise authorized under this section and the 16:34 Feb 20, 2009 Jkt 217001 BILLING CODE 9111–97–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0952; Directorate Identifier 98–ANE–49–AD; Amendment 39– 15816; AD 2009–04–10] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF6–80A, CF6–80C2, and CF6–80E1 Series Turbofan Engines The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6– 80A, CF6–80C2, and CF6–80E1 series turbofan engines. That AD required 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 piecepart exposure. This AD requires 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 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. SUMMARY: § 274a.2 Verification of identity and employment authorization. VerDate Nov<24>2008 Janet Napolitano, Secretary. [FR Doc. E9–3801 Filed 2–19–09; 11:15 am] AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. Authority: 8 U.S.C. 1101, 1103, 1324a; 8 CFR part 2. * immigration laws. An alien described in this section is not issued an employment authorization document. This AD becomes effective March 30, 2009. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground DATES: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 7995 Floor, Room W12–140, Washington, DC 20590–0001. 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: The FAA proposed to amend 14 CFR part 39 by superseding AD 2002–07–12, Amendment 39–12707 (67 FR 17279, April 10, 2002), with a proposed AD. The proposed AD applies to GE CF6– 80A, CF6–80C2, and CF6–80E1 series turbofan engines. We published the proposed AD in the Federal Register on October 23, 2008 (73 FR 63090). That action proposed to 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. 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 one comment received. ABX Air requests that we add a statement to the AD, acknowledging that previously approved alternative methods of compliance (AMOCs) for AD 2002–07–12, the AD being superseded, are also approved for this AD. We agree and added that statement to the AD. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the E:\FR\FM\23FER1.SGM 23FER1 7996 Federal Register / Vol. 74, No. 34 / Monday, February 23, 2009 / Rules and Regulations Regulatory Findings economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 315 CF6–80A series engines and 926 CF6–80C2 series engines installed on airplanes of U.S. registry. We also estimate that it will take about 5 workhours per CF6–80A series engine and about 2 work-hours per CF6–80C2 series engine to do the 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 will be about $400. The total cost of the new inspections per CF6–80C2 series engine will 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. 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, Safety. 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: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–12707 (67 FR 17279, April 10, 2002), and by adding a new airworthiness directive, ■ 2009–04–10 General Electric Company: Amendment 39–15816. Docket No. FAA–2008–0952; Directorate Identifier 98–ANE–49–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 30, 2009. 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 Adoption of the Amendment § 39.13 Amendment 39–15816, to read as follows: (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: Part number (P/N) Inspect per engine manual inspection chapter For CF6–80A Engines: Disk, Fan Rotor, Stage 1 ................................... mstockstill on PROD1PC66 with RULES Part nomenclature All ........................ 72–21–03 Paragraph 3. Fluorescent-Penetrant Inspect, and 72–21–03 Paragraph 4. Eddy Current Inspect. 72–21–05 Paragraph 2. Magnetic Particle Inspect. 72–24–01 Paragraph 2. Magnetic Particle Inspect. 72–31–04 Paragraph 3. Fluorescent-Penetrant Inspect. 72–31–05 Paragraph 4. Fluorescent-Penetrant Inspect. 72–31–06 Paragraph 3. Fluorescent-Penetrant Inspect. 72–31–07 Paragraph 3. Fluorescent-Penetrant Inspect. 72–31–08 Paragraph 3.A. Fluorescent-Penetrant Inspect. 72–31–10 Paragraph 3. Fluorescent-Penetrant Inspect. 72–53–02 Paragraph 3. 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. Fan Forward Shaft ............................................. Fan Mid Shaft ..................................................... Disk, HPC Rotor, Stage One ............................. **Disk, HPC Rotor, Stage Two .......................... Spool, HPC Rotor, Stage 3–9 ............................ Disk, HPC Rotor, Stage 10 ................................ Spool, HPC Rotor, Stage 11–14 ........................ Rotating CDP Seal ............................................. Disk Shaft, HPT Rotor, Stage One .................... VerDate Nov<24>2008 16:34 Feb 20, 2009 Jkt 217001 PO 00000 All All All All All All All All All ........................ ........................ ........................ ........................ ........................ ........................ ........................ ........................ ........................ Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\23FER1.SGM 23FER1 Federal Register / Vol. 74, No. 34 / Monday, February 23, 2009 / Rules and Regulations 7997 Part number (P/N) Inspect per engine manual inspection chapter *Disk Shaft, HPT Rotor, Stage One .................. All ........................ *Disk Shaft, HPT Rotor, Stage One .................. Disk, HPT Rotor, Stage Two ............................. P/Ns 2047M33G01 thru G10, and P/N 9362M58G11. All ........................ 72–53–02 Paragraph 6.E. Disk Dovetail Slot Bottom Eddy Current Inspection. 72–53–02 Paragraph 7. Disk Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection. Disk, LPT Rotor, Stage 1–4 ............................... Shaft, LPT Rotor ................................................ All ........................ All ........................ For All CF6–80C2 Engines: Disk, Fan Rotor, Stage 1 ................................... All ........................ Shaft, Fan Forward ............................................ All ........................ Fan Mid Shaft ..................................................... HPCR Stage 1 Disk ........................................... HPCR Stage 2 Disk ........................................... HPCR Stage 3–9 Spool ..................................... HPCR Stage 10 Disk ......................................... HPCR Stage 11–14 Spool/Shaft ........................ No. 4 Bearing Rotating (CDP) Air Seal ............. All All All All All All All HPCR Stage 10–14 Spool/Shaft ........................ ** Disk/Shaft, HPT Rotor, Stage One ................. All ........................ All ........................ * Disk/Shaft, HPT Rotor, Stage One .................. Disk, HPT Rotor, Stage Two ............................. P/N 1531M84G12 and P/Ns 2047M32G01 thru G07. All ........................ LPTR Stage 1–5 Disks ...................................... LPTR Shaft ......................................................... All ........................ All ........................ Part nomenclature For CF6–80C2 Engines configured with the R88DT Turbine (Models CF6–80C2B2F, 80C2B4F, 80C2B6F, 80C2B7F, 80C2B8F): Disk/Shaft, HPT Rotor, Stage One (R88DT, No Rim Bolt Holes). Disk, HPT Rotor, Stage Two (R88DT, No Rim Bolt Holes). ........................ ........................ ........................ ........................ ........................ ........................ ........................ mstockstill on PROD1PC66 with RULES 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. Task 72–21–05–200–000–001 Fluorescent Penetrant Inspection, and Task 72–21–05–200–000–005 Vent Hole Eddy Current Inspection. Task 72–24–01–200–000–003 Magnetic Particle Inspection. Task 72–31–04–200–000–002 Fluorescent Penetrant Inspection. Task 72–31–05–200–000–002 Fluorescent Penetrant Inspection. Task 72–31–06–200–000–001 Fluorescent Penetrant Inspection. Task 72–31–07–200–000–001 Fluorescent Penetrant Inspection. Task 72–31–08–200–000–002 Fluorescent Penetrant Inspection. Task 72–31–10–200–000–001 Fluorescent Penetrant Inspection or Task 72–31–10–200–000-A01 Fluorescent Penetrant Inspection. Task 72–31–22–200–000–002 Fluorescent Penetrant Inspection. Task 72–53–02–200–000–001 (Inspection—Configuration 1), or Task 72–53–02–230–801 (Inspection—Configuration 2), FluorescentPenetrant 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. Task 72–53–02–250–801 (Inspection—Configuration 1), Disk Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection. 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. Task 72–57–02–200–000–001 Fluorescent-Penetrant Inspection. Task 72–57–03–200–000–002 Fluorescent-Penetrant Inspect, and Task 72–57–03–200–000–006 Eddy Current Inspection. All ........................ All ........................ For CF6–80E1 Engines: Disk, Fan Rotor, Stage One .............................. All ........................ Shaft, Fan ........................................................... All ........................ PO 00000 Disk Bore Eddy Current Inspection. Fluorescent-Penetrant Inspection. Fluorescent-Penetrant Inspection, and Eddy Current Inspection. Task 72–53–16–200–000–005 Disk Bore Area Eddy Current Inspection. Task 72–53–18–200–000–002 Fluorescent-Penetrant Inspect, and Forward Outer Seal (R88DT) ............................. Jkt 217001 7. 3. 3. 6. Task 72–53–16–200–000–001 Fluorescent-Penetrant Inspect, and All ........................ 16:34 Feb 20, 2009 3. Fluorescent-Penetrant Inspection, and 6. Eddy Current Inspection of Rim Bolt Holes for All ........................ Rotating Interstage Seal (R88DT) ..................... VerDate Nov<24>2008 72–53–06 Paragraph 72–53–06 Paragraph Cracks, and 72–53–06 Paragraph 72–57–02 Paragraph 72–57–03 Paragraph 72–57–03 Paragraph Frm 00005 Fmt 4700 Task 72–53–18–200–000–005 Disk Bore Area Eddy Current Inspection. Task 72–53–17–200–000–001 Fluorescent-Penetrant Inspect, and Task 72–53–17–200–000–005 Seal Bore Area Eddy Current. Task 72–53–21–200–000–001 Fluorescent-Penetrant Inspect, and Task 72–53–21–200–000–004 Seal Bore Area Eddy Current. 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. Sub Task 72–21–05–230–051 Fluorescent Penetrant Inspection, and Sub Task 72–21–05–250–051 Vent Hole Eddy Current Inspection. Sfmt 4700 E:\FR\FM\23FER1.SGM 23FER1 7998 Federal Register / Vol. 74, No. 34 / Monday, February 23, 2009 / Rules and Regulations Part number (P/N) Part nomenclature Compressor Rotor, Stage 1 Disk ....................... Compressor Rotor, Stage 2 Disk ....................... Compressor Rotor, Stage 3–9 Spool ................. Compressor Rotor, Stage 10 Disk (Pre SB 72– 0150). Compressor Rotor Spool/Shaft, Stage 11–14 (Pre SB 72–0150). Compressor Rotor Spool/Shaft, Stage 10–14 (SB 72–0150). Compressor Rotor No. 4 Bearing Rotating Air Seal (CDP Rotating Seal). HPT Disk/Shaft, Stage 1 .................................... All All All All HPT Disk, Stage 2 ............................................. All ........................ LPT Rotor Shaft ................................................. LPT Disks, Stages 1–5 ...................................... LPT Rotor Torque Cone .................................... For CF6–80E1 Engines configured with the R88DT Turbine: Disk/Shaft, HPT Rotor, Stage 1 (R88DT, No Rim Bolt Holes). Disk, HPT Rotor, Stage 2 (R88DT, No Rim Bolt Holes). ........................ ........................ ........................ ........................ mstockstill on PROD1PC66 with RULES Jkt 217001 Penetrant Penetrant Penetrant Penetrant Inspection. Inspection. Inspection. Inspection. All ........................ Sub Task 72–31–10–230–051 Fluorescent Penetrant Inspection. All ........................ All ........................ All ........................ 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. 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. Sub Task 72–55–01–240–051 Magnetic Particle Inspect. Sub Task 72–57–02–230–051 Fluorescent-Penetrant Inspect. Sub Task 72–57–03–220–051 Fluorescent-Penetrant Inspect. All ........................ Sub Task 72–53–16–230–052 Fluorescent-Penetrant Inspect, and All ........................ Sub Task 72–53–16–250–051 Disk Bore Area Eddy Current Inspection. Sub Task 72–53–18–230–051 Fluorescent-Penetrant Inspect, and Sub Task 72–53–18–250–051 Disk Bore Area Eddy Current Inspection. Sub Task 72–53–17–230–056 Fluorescent-Penetrant Inspect, and Sub Task 72–53–17–250–051 Seal Bore Area Eddy Current. Sub Task 72–53–21–230–051 Fluorescent-Penetrant Inspect, and Sub Task 72–53–21–250–051 Seal Bore Area Eddy Current. 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. (k) AMOCs previously approved for AD 2002–07–12, are also approved for this AD. Maintaining Records of the Mandatory Inspections (l) 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 PO 00000 Fluorescent Fluorescent Fluorescent Fluorescent Sub Task 72–31–23–230–052 Fluorescent Penetrant Inspection. All ........................ 16:34 Feb 20, 2009 72–31–04–230–051 72–31–05–230–051 72–31–06–230–051 72–31–07–230–051 All ........................ HPT Rotor Forward Outer Seal (R88DT) .......... VerDate Nov<24>2008 Task Task Task Task Sub Task 72–31–08–230–051 Fluorescent Penetrant Inspection. All ........................ 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 Sub Sub Sub Sub All ........................ ** HPT Rotor Rotating Interstage Seal (R88DT) (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. Inspect per engine manual inspection chapter Frm 00006 Fmt 4700 Sfmt 4700 (2) Meets the requirements of section 121.369(c); and (3) Maintains the records either indefinitely or until the work is repeated. (m) 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 record keeping requirements do not alter or amend the record keeping requirements for any other AD or regulatory requirement. Related Information (n) 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. Material Incorporated by Reference (o) None. Issued in Burlington, Massachusetts, on February 5, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate. [FR Doc. E9–3105 Filed 2–20–09; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\23FER1.SGM 23FER1

Agencies

[Federal Register Volume 74, Number 34 (Monday, February 23, 2009)]
[Rules and Regulations]
[Pages 7995-7998]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3105]

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

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0952; Directorate Identifier 98-ANE-49-AD;
Amendment 39-15816; AD 2009-04-10]
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: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for General Electric Company (GE) CF6-80A, CF6-80C2, and CF6-80E1
series turbofan engines. That AD required 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 AD requires 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 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.

DATES: This AD becomes effective March 30, 2009.

ADDRESSES: 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: 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: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2002-07-12, Amendment 39-12707 (67 FR 17279, April 10,
2002), with a proposed AD. The proposed AD applies to GE CF6-80A, CF6-
80C2, and CF6-80E1 series turbofan engines. We published the proposed
AD in the Federal Register on October 23, 2008 (73 FR 63090). That
action proposed to 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.

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 one comment received.
ABX Air requests that we add a statement to the AD, acknowledging
that previously approved alternative methods of compliance (AMOCs) for
AD 2002-07-12, the AD being superseded, are also approved for this AD.
We agree and added that statement to the AD.

Conclusion

We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the change described previously.
We have determined that this change will neither increase the

[[Page 7996]]

economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

We estimate that this AD will affect 315 CF6-80A series engines and
926 CF6-80C2 series engines installed on airplanes of U.S. registry. We
also estimate that it will take about 5 work-hours per CF6-80A series
engine and about 2 work-hours per CF6-80C2 series engine to do the
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
will be about $400. The total cost of the new inspections per CF6-80C2
series engine will 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 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, 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 removing Amendment 39-12707 (67 FR
17279, April 10, 2002), and by adding a new airworthiness directive,
Amendment 39-15816, to read as follows:

2009-04-10 General Electric Company: Amendment 39-15816. Docket No.
FAA-2008-0952; Directorate Identifier 98-ANE-49-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective March
30, 2009.

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:

----------------------------------------------------------------------------------------------------------------
Part nomenclature Part number (P/N) Inspect per engine 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 One.. All...................... 72-53-02 Paragraph 3. 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.

[[Page 7997]]

*Disk Shaft, HPT Rotor, Stage One. All...................... 72-53-02 Paragraph 6.E. Disk Dovetail Slot
Bottom Eddy Current Inspection.
*Disk Shaft, HPT Rotor, Stage One. P/Ns 2047M33G01 thru G10, 72-53-02 Paragraph 7. Disk Dovetail Slot
and P/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) Air All...................... Task 72-31-10-200-000-001 Fluorescent
Seal. 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, Stage All...................... Task 72-53-02-200-000-001 (Inspection--
One. 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 One P/N 1531M84G12 and P/Ns Task 72-53-02-250-801 (Inspection--
2047M32G01 thru G07. Configuration 1), Disk 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 One All...................... Task 72-53-16-200-000-001 Fluorescent-
(R88DT, No Rim Bolt Holes). Penetrant Inspect, and
Task 72-53-16-200-000-005 Disk Bore Area Eddy
Current Inspection.
Disk, HPT Rotor, Stage Two (R88DT, All...................... Task 72-53-18-200-000-002 Fluorescent-
No Rim Bolt Holes). Penetrant Inspect, and
Task 72-53-18-200-000-005 Disk Bore Area Eddy
Current Inspection.
Rotating Interstage Seal (R88DT).. All...................... Task 72-53-17-200-000-001 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.

[[Page 7998]]

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.
Compressor Rotor, Stage 3-9 Spool. All...................... Sub Task 72-31-06-230-051 Fluorescent
Penetrant Inspection.
Compressor Rotor, Stage 10 Disk All...................... Sub Task 72-31-07-230-051 Fluorescent
(Pre SB 72-0150). Penetrant Inspection.
Compressor Rotor Spool/Shaft, All...................... Sub Task 72-31-08-230-051 Fluorescent
Stage 11-14 (Pre SB 72-0150). Penetrant Inspection.
Compressor Rotor Spool/Shaft, All...................... Sub Task 72-31-23-230-052 Fluorescent
Stage 10-14 (SB 72-0150). Penetrant Inspection.
Compressor Rotor No. 4 Bearing All...................... Sub Task 72-31-10-230-051 Fluorescent
Rotating Air Seal (CDP Rotating Penetrant Inspection.
Seal).
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 72-53-16-230-052 Fluorescent-
(R88DT, No Rim Bolt Holes). Penetrant Inspect, and
Sub Task 72-53-16-250-051 Disk Bore Area Eddy
Current Inspection.
Disk, HPT Rotor, Stage 2 (R88DT, All...................... Sub Task 72-53-18-230-051 Fluorescent-
No Rim Bolt Holes). Penetrant Inspect, and
Sub Task 72-53-18-250-051 Disk Bore Area Eddy
Current Inspection.
** HPT Rotor Rotating Interstage All...................... Sub Task 72-53-17-230-056 Fluorescent-
Seal (R88DT). Penetrant Inspect, and
Sub Task 72-53-17-250-051 Seal Bore Area Eddy
Current.
HPT Rotor Forward Outer Seal All...................... Sub Task 72-53-21-230-051 Fluorescent-
(R88DT). 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.
(k) AMOCs previously approved for AD 2002-07-12, are also
approved for this AD.

Maintaining Records of the Mandatory Inspections

(l) 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.
(m) 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 record keeping requirements do not alter or
amend the record keeping requirements for any other AD or regulatory
requirement.

Related Information

(n) 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.

Material Incorporated by Reference

(o) None.

Issued in Burlington, Massachusetts, on February 5, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate.
[FR Doc. E9-3105 Filed 2-20-09; 8:45 am]
BILLING CODE 4910-13-P

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