E8-25278. 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: [phone].

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: [e-mail]; telephone [phone].

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 [phone]) 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. 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.

§ 39.13

[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 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:

Part nomenclature	Part No. (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.
* 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, and P/N 9362M58G11	72-53-02 Paragraph 7. Disk Dovetail Slot 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 Seal	All	Task 72-31-10-200-000-001 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, Stage One	All	Task 72-53-02-200-000-001 (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 One	P/N 1531M84G12 and P/Ns 2047M32G01 thru G07	Task 72-53-02-250-801 (Inspection—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 (R88DT, No Rim Bolt Holes)	All	Task 72-53-16-200-000-001 Fluorescent-Penetrant Inspect, and
		Task 72-53-16-200-000-005 Disk Bore Area Eddy Current Inspection.
Disk, HPT Rotor, Stage Two (R88DT, No Rim Bolt Holes)	All	Task 72-53-18-200-000-002 Fluorescent-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.
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 (Pre SB 72-0150)	All	Sub Task 72-31-07-230-051 Fluorescent Penetrant Inspection.
Compressor Rotor Spool/Shaft, Stage 11-14 (Pre SB 72-0150)	All	Sub Task 72-31-08-230-051 Fluorescent Penetrant Inspection.
Compressor Rotor Spool/Shaft, Stage 10-14 (SB 72-0150)	All	Sub Task 72-31-23-230-052 Fluorescent Penetrant Inspection.
Compressor Rotor No. 4 Bearing Rotating Air Seal (CDP Rotating Seal)	All	Sub Task 72-31-10-230-051 Fluorescent 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 (R88DT, No Rim Bolt Holes)	All	Sub Task 72-53-16-230-052 Fluorescent-Penetrant Inspect, and
		Sub Task 72-53-16-250-051 Disk Bore Area Eddy Current Inspection.
Disk, HPT Rotor, Stage 2 (R88DT, No Rim Bolt Holes)	All	Sub Task 72-53-18-230-051 Fluorescent-Penetrant Inspect, and
		Sub Task 72-53-18-250-051 Disk Bore Area Eddy Current Inspection.
** HPT Rotor Rotating Interstage Seal (R88DT)	All	Sub Task 72-53-17-230-056 Fluorescent-Penetrant Inspect, and
		Sub Task 72-53-17-250-051 Seal Bore Area Eddy Current.
HPT Rotor Forward Outer Seal (R88DT)	All	Sub Task 72-53-21-230-051 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: [e-mail]; telephone [phone]; fax [phone], for more information about this AD.

Issued in Burlington, Massachusetts, on October 16, 2008.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.