Airworthiness directives: General Electric Co.,

[Federal Register: August 18, 2006 (Volume 71, Number 160)]

[Rules and Regulations]

[Page 47717-47725]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr18au06-8]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-NE-05-AD; Amendment 39-14706; AD 2006-16-06]

RIN 2120-AA64

Airworthiness Directives; General Electric Company (GE) CF6-80 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION: Final rule; request for comments.

SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for GE CF6-80 series turbofan engines with certain stage 1 high- pressure turbine (HPT) rotor disks. That AD currently requires an initial inspection as a qualification for the mandatory rework procedures for certain disks, and repetitive inspections only for certain disks for which the rework procedures were not required. That action also requires reworking certain disks before further flight, and removes certain CF6-80E1 series disks from service. This AD requires the same actions but shortens the compliance schedule for HPT disks that have not been previously inspected using AD 2004-04-07, which this AD supersedes. This AD results from a recent report of an uncontained failure of a stage 1 HPT disk. We are issuing this AD to detect and prevent cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure.

DATES: Effective September 5, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of September 5, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain other publications listed in the regulations as of March 12, 2004 (69 FR 8801, February 26, 2004).

We must receive any comments on this AD by October 17, 2006.

ADDRESSES: Use one of the following addresses to submit comments on this ad:

By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2004-NE-05-AD, 12 New England Executive Park, Burlington, MA 01803.

By fax: (781) 238-7055.

By e-mail: 9-ane-adcomment@faa.gov.

Contact General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672-8400, fax (513) 672-8422, for the service information identified in this AD.

You may examine the AD docket, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service information, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone: (781) 238- 7176, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: On February 13, 2004, we issued AD 2004-04- 07, Amendment 39-13488 (69 FR 38; February 26, 2004). That AD requires an initial inspection as a qualification for the mandatory rework procedures for certain disks, and repetitive inspections only for certain disks for which the rework procedures were not required. That action also requires reworking certain disks before further flight. That AD was the result of the manufacturer's investigation and development of a rework procedure to chamfer the aft breakedge of the dovetail slot bottom to reduce stresses. That condition, if not corrected, could result in cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure.

Actions Since AD 2004-04-07 Was Issued

Since AD 2004-04-07 was issued, a CF6-80A turbofan engine, installed on a Boeing 767 airplane, experienced an uncontained stage 1 HPT disk failure on June 2, 2006. The disk failure resulted in a fire and significant damage to the airplane. The event occurred during an on-ground maintenance operation.

Relevant Service Information

We reviewed and approved the technical contents of the following GE Service Bulletins (SBs) and Alert Service Bulletin (ASB) that describe procedures for removing, inspecting, and reworking certain stage 1 HPT rotor disks:

SB No. CF6-80E1 S/B 72-0251, dated January 22, 2004;

SB No. CF6-80A S/B 72-0779, Revision 1, dated January 22, 2004;

SB No. CF6-80A S/B 72-0788, Revision 3, dated July 20, 2006;

SB No. CF6-80A S/B 72-0822, dated July 20, 2006;

ASB No. CF6-80C2 S/B 72-A1026, Revision 2, dated January 22, 2004;

SB No. CF6-80C2 S/B 72-1089, Revision 3, dated July 20, 2006;

SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006.

FAA's Determination and Requirements of This AD

The unsafe condition described previously is likely to exist or develop on other GE CF6-80 series turbofan engines of the same type design. This AD requires rework of the dovetail slot bottom of certain stage 1 rotor disks. The disks must pass an inspection to qualify for the rework. This AD also requires removal from service of certain disks for which the rework procedures were not previously required. This AD also tightens the compliance schedule for HPT disks that have not been previously inspected using AD 2004-04-07. Operators must use the compliance schedule carried forward from AD 2004-04-07 or the new compliance schedule below, whichever occurs first:

For stage 1 HPT rotor disks with 9,000 or more cycles- since-new (CSN) on the effective date of this AD, within 250 cycles-in- service (CIS) after the effective date of this AD, or by March 31, 2007, whichever occurs first.

For stage 1 HPT rotor disks with 6,900 or more but fewer than 9,000 CSN on the effective date of this AD, within 500 CIS after the effective date of this AD, or before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first.

For stage 1 HPT rotor disk with fewer than 6,900 CSN on the effective date of this AD, before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first.

This AD also removes from service certain CF6-80E1 series disks. You must use the service information described previously to perform the actions required by this AD.

[[Page 47718]]

FAA's Determination of the Effective Date

Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ``AD Docket No. 2004-NE-05-D'' in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us verbally, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments.

Examining the AD Docket

You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location.

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 the regulation:

  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. 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 by sending a request to us at the address listed under ADDRESSES. Include ``AD Docket No. 2004-NE-05-AD'' in your request.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0 Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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 39-13488 (69 FR 8801; February 26, 2004), and by adding a new airworthiness directive, Amendment 39-14706, to read as follows:

2006-16-06 General Electric Company: Amendment 39-14706. Docket No. 2004-NE-05-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective September 5, 2006.

Affected ADs

(b) This AD supersedes AD 2004-04-07 (69 FR 8801; February 26, 2004).

Applicability

(c) This AD applies to the General Electric Company (GE) CF6-80 turbofan engine models listed in the following Table 1:

Table 1.--Applicability Models, Part Numbers, Airplanes

Stage 1 high pressure turbine Engines installed Models

(HPT) rotor disk on but not limited part numbers (P/

to Ns)

CF6-80A, CF6-80A1, CF6-80A2, CF6- 9234M67G22/G24/G25/ Airbus A310 and 80A3.

G26, 9362M58G02/ Boeing 767 G06/G07/G09,

airplanes. 9367M45G02/G04/ G09. CF6-80C2A1, CF6-80C2A2, CF6- 1862M23G01,

Airbus A300, A310, 80C2A3, CF6-80C2A5, CF6-80C2A8, 9392M23G10/G12/ Boeing 747, 767, CF6-80C2A5F, CF6-80C2B1, CF6- G21, 1531M84G02/ and McDonnell 80C2B2, CF6-80C2B4, CF6-80C2B6, G06/G08/G10/G12. Douglas MD11 CF6-80C2B1F, CF6-80C2B2F, CF6-

airplanes. 80C2B4F, CF6-80C2B5F, CF6- 80C2B6F, CF6-80C2B6FA, CF6- 80C2B7F, CF6-80C2D1F. CF6-80E1A2, CF6-80E1A4.......... 1639M41P04........ Airbus A330 airplanes.

These engines are installed on, but not limited to, the airplanes listed in Table 1 of this AD.

Unsafe Condition

(d) This AD results from a recent report of an uncontained failure of a stage 1 HPT disk. The actions specified in this AD are intended to detect and prevent cracks in the bottoms of the dovetail slots that could propagate to

[[Page 47719]]

failure of the disk and cause an uncontained engine failure.

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.

CF6-80A, -80A1, -80A2, and -80A3 Engines

Stage 1 HPT Rotor Disks, P/N 9362M58G09, With Chamfered Breakedges

(f) At the next piece-part exposure, for stage 1 HPT rotor disks, P/N 9362M58G09, with serial numbers (SNs) listed in Table 2 of this AD, do the following, unless already done using superseded AD 2004-04-07:

Table 2.--SNs of CF6-80A Series Stage 1 HPT Rotor Disk P/N 9362M58G09-- With Chamfered Breakedges

GWN03RD7 GWN03TKG GWN03TKH GWN03TKJ GWN03W3M GWN03W3N GWN03W3R GWN042J3 GWN04FW2 GWN04FW3 GWN04FW4 GWN04FW5 GWN04H0M GWN04HRA GWN04HRD GWN04HRE GWN04HRF GWN04HRG GWN04HRH GWN04K8N GWN04M9J GWN04M9K GWN04M9L GWN04M9M GWN04M9R GWN04M9T GWN04M9W

(1) Visually inspect the rotor disks for the presence of a chamfer on the aft breakedges of the dovetail slot bottoms. Use paragraph 3.A. of GE Service Bulletin (SB) No. CF6-80A S/B 72-0822, dated July 20, 2006, to do the inspection.

(2) For disks that have the chamfered breakedges, re-mark, fluorescent penetrant inspect (FPI), and eddy current inspect (ECI) the rotor disk. Use paragraph 3.A.(1) of the Accomplishment Instructions of GE SB No. CF6-80A S/B 72-0822, dated July 20, 2006, to re-mark and inspect the rotor disk and remove from service as necessary.

(3) For disks that do not have the chamfered breakedges, remove the disk from service. Use paragraph 3.A(2) of the Accomplishment Instructions of GE SB No. CF6-80A S/B 72-0822, dated July 20, 2006.

Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 with SNs not listed in Table 2 of this AD

(g) For stage 1 HPT rotor disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 with SNs not listed in Table 2 of this AD, inspect, rework, and re-mark the disks using paragraphs 3.A.(1) through 3.A.(2) of Accomplishment Instructions of GE SB No. CF6-80A S/B 72-0788, Revision 3, dated July 20, 2006, at the following, unless already done using superseded AD 2004-04-07:

(1) For both new and used stage 1 HPT rotor disks not installed in engines, inspect, rework, re-mark, and remove from service as necessary before further flight.

(2) For stage 1 HPT rotor disks that have been inspected using any version of GE SB No. CF6-80A S/B 72-0779, inspect, rework, re- mark, and remove from service as necessary at the next Engine Shop Visit (ESV) using the compliance times in the following Table 3:

Table 3.--Compliance Times for Inspection and Rework of CF6-80A Series Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 With SNs Not Listed in Table 2 of This AD--Previously Inspected

Stage 1 HPT rotor disk cycles-since- last-inspection (CSLI) on March 12, Compliance time for inspection 2004 (effective date of superseded AD

and rework 2004-04-07)

(i) More than 1,500 CSLI............... At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 4,500 CSLI. (ii) 1,500 CSLI or fewer............... At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 3,500 CSLI.

(3) For stage 1 HPT rotor disks which have not been inspected using any version of GE SB No. CF6-80A S/B 72-0779, inspect, rework, re-mark, and remove from service as necessary using the following Table 4 or Table 4A compliance times, whichever occurs first:

Table 4.--Compliance Times for Inspection and Rework of CF6-80A Series Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 With SNs Not Listed in Table 2 of This AD--Not Previously Inspected

Stage 1 HPT rotor disk cycles-since-new Compliance time for inspection (CSN) on the effective date of this AD

and rework

(i) 9,000 or more CSN.................. Within 250 cycles-in-service (CIS) after the effective date of this AD, or by March 31, 2007, whichever occurs first. (ii) 6,900 or more but fewer than 9,000 Within 500 CIS after the CSN.

effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first. (iii) Fewer than 6,900 CSN............. Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first.

[[Page 47720]]

Table 4A.--Compliance Times for Inspection and Rework of CF6-80A Series Stage 1 HPT Rotor Disks, P/Ns 9234M67G22, G24, G25, G26, 9367M45G04, G09, 9362M58G02, G06, G07, and 9362M58G09 With SNs Not Listed in Table 2 of This AD--Not Previously Inspected

Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD Compliance time for inspection 2004-04-07)

and rework

(i) 10,000 or more CSN................. At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first. (ii) 5,000 or more CSN but fewer than At the next ESV or within 2,400 10,000 CSN.

CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 11,000 CSN. (iii) Fewer than 5,000 CSN............. At the next ESV or within 3,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 7,400 CSN.

Stage 1 HPT Rotor Disks, P/N 9367M45G02

(h) For stage 1 HPT rotor disks, P/N 9367M45G02, remove the disk from service at the following times:

(1) For stage 1 HPT rotor disks not installed in engines, remove from service before further flight.

(2) For stage 1 HPT rotor disks that have been inspected before the effective date of this AD using any version of GE SB No. CF6-80A S/B 72-0779, and had more than zero CSN at the time of that inspection, remove from service at next ESV.

(3) For stage 1 HPT rotor disks that have not been inspected, or were only inspected with zero CSN before the effective date of this AD using any version of GE SB No. CF6-80A S/B 72-0779, remove from service using the following Table 5 or Table 5A compliance times, whichever occurs first:

Table 5.--Compliance Times for Removal of CF6-80A Series Stage 1 HPT Rotor Disks, P/N 9367M45G02--Not Previously Inspected

Stage 1 HPT rotor disk CSN on the effective date of this AD

Compliance time for removal

(i) 9,000 or more CSN.................. Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first. (ii) 6,900 or more but fewer than 9,000 Within 500 CIS after the CSN.

effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first. (iii) Fewer than 6,900 CSN............. Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first.

Table 5A.--Compliance Times for Removal of CF6-80A Series Stage 1 HPT Rotor Disks, P/N 9367M45G02--Not Previously Inspected

Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD Compliance time for removal 2004-04-07)

(i) 10,000 or more CSN................. At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first. (ii) 5,000 or more CSN but fewer than At the next ESV or within 2,400 10,000 CSN.

CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 11,000 CSN. (iii) Fewer than 5,000 CSN............. At the next ESV or within 3,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 7,400 CSN.

CF6-80C2 Series Engines

Stage 1 HPT Rotor Disks, P/N 1531M84G10, With Chamfered Breakedges, Group 1

(i) At the next piece-part exposure, for stage 1 HPT rotor disks, P/N 1531M84G10, with SNs listed in Table 6 (Group 1) of this AD, do the following, unless already done using superseded AD 2004- 04-07:

Table 6.--SNs of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1531M84G10, With Chamfered Breakedges, Group 1

GWN03111 GWN03114 GWN031N2 GWN031N3 GWN031N4 GWN031N5 GWN031N6 GWN031N7 GWN031N8 GWN031N9 GWN031NA GWN031NC GWN032G1 GWN032G2 GWN032G3 GWN032G4 GWN032G5 GWN032G6 GWN032G7 GWN032G8 GWN032G9 GWN032GE GWN0335P GWN0335R GWN033C5 GWN034KR GWN034KT GWN03501 GWN0350M GWN0350N GWN0350P

[[Page 47721]]

GWN0350R GWN0350T GWN0350W GWN035M5 GWN035M6 GWN035M7 GWN035M8 GWN035M9 GWN035MA GWN035MC GWN035MD GWN035TH GWN035TJ GWN035TK GWN035TL GWN035TM GWN03699 GWN0369A GWN0369C GWN0369D GWN0369E GWN0369G GWN0369H GWN0369J GWN036JG GWN036JH GWN036JJ GWN036JK GWN036JL GWN036JM GWN036JN GWN03752 GWN03753 GWN03754 GWN03755 GWN03756 GWN03757 GWN03759 GWN0375A GWN0375C GWN0375D GWN0375E GWN037H2 GWN03981 GWN03982 GWN03983 GWN03984 GWN03985 GWN03986 GWN03987 GWN03988 GWN03989 GWN0398A GWN0398C GWN039PF GWN039PG GWN039PH GWN039PJ GWN039PK GWN039PL GWN039PM GWN039PN GWN03A4J GWN03A4K GWN03A4L GWN03A4M GWN03A4N GWN03A4P GWN03A4R GWN03A4T GWN03A4W GWN03C12 GWN03C13 GWN03C14 GWN03CA0 GWN03DC9 GWN03DCA GWN03DCC GWN03DCD GWN03DCE GWN03DCF GWN03DCG GWN03DCH GWN03DCJ GWN03DCK GWN03DCL GWN03DCM GWN03DCN GWN03DCP GWN03DCR GWN03DME GWN03DMF GWN03ER7 GWN03ER8 GWN03ER9 GWN03ERA GWN03FTN GWN03FTP GWN03FTR GWN03FTT GWN03FTW GWN03FW0 GWN03H56 GWN03H57 GWN03H58 GWN03HTL GWN03HTM GWN03HTN GWN03HTP GWN03HTR GWN03HTT GWN03J8T GWN03J8W GWN03J91 GWN03J92 GWN03JNN GWN03JNP GWN03K3C GWN03K3D GWN03K3F GWN03K3G GWN03K3H GWN03K3K GWN03K3L GWN03K3M GWN03K3N GWN03K3T GWN03K3W GWN03K40 GWN03K7R GWN03KR1 GWN03KR3 GWN03KR4 GWN03KR6 GWN03KR7 GWN03KR8 GWN03KRC GWN03L2D GWN03L2E GWN03L2F GWN03LNF GWN03LNJ GWN03LNK GWN03M88 GWN03M8C GWN03M8E GWN03M8J GWN03M8K GWN03NHN GWN03NHP GWN03NHR GWN03R74 GWN03R76 GWN03R78 GWN03R7E GWN03R7F GWN03R9G GWN03R9H GWN03R9M GWN03R9P GWN03R9T GWN03RA2 GWN03RA3 GWN03RA5 GWN03RA8 GWN03RPA GWN03RPC GWN03RPD GWN04026 GWN0402A GWN0402F GWN0402L GWN040R5 GWN04189 GWN0418A GWN0418D GWN0418E GWN0418F GWN0418H GWN0418J GWN0418L GWN0418N GWN0418R GWN04366 GWN044DP GWN0454H GWN0454M GWN0454N GWN045T0 GWN045T2 GWN045T8 GWN045TD GWN045TG GWN04722 GWN04729 GWN047LK GWN048CD GWN048CF GWN048CH GWN048CJ GWN048CK GWN049GJ GWN049M8 GWN049M9 GWN04AER GWN04ALR GWN04AM1 GWN04CGJ GWN04CGN GWN04CGT GWN04CGW GWN04CH3 GWN04CH5

[[Page 47722]]

GWN04CH8 GWN04CH9 GWN04D52 GWN04D54 GWN04D56 GWN04D57 GWN04D58 GWN04D59 GWN04DPW GWN04E9K GWN04E9L GWN04E9M GWN04EMA GWN04EMK GWN04EML GWN04EMM GWN04FTL GWN04FTM GWN04FTN

(1) Visually inspect the rotor disks for the presence of a chamfer on the aft breakedges of the dovetail slot bottoms. Use paragraph 3.A. of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to do the inspection.

(2) For disks that have the chamfered breakedges, re-mark, FPI, and ECI the rotor disk. Use paragraph 3.A.(1) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to re-mark and inspect the rotor disk, and remove from service as necessary.

(3) For disks that do not have the chamfered breakedges, remove the disk from service. Use paragraph 3.A.(4) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006.

CF6-80C2 Series Engines

Stage 1 HPT Rotor Disks, P/N 1531M84G10, With Chamfered Breakedges, Group 2

(j) For stage 1 HPT rotor disks, P/N 1531M84G10, with SNs listed in Table 6A of this AD, with chamfered breakedges, (Group 2):

(1) With more than 6,900 CSN, perform paragraphs (j)(3) through (j)(5) as applicable, at the next ESV, but within 500 CIS after the effective date of this AD, unless already done using superseded AD 2004-04-07.

(2) With 6,900 CSN or fewer, perform paragraphs (j)(3) through (j)(5) as applicable, at the next ESV, but before accumulating 7,400 CSN, unless already done using superseded AD 2004-04-07.

Table 6A.--SNs of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1531M84G10, With Chamfered Breakedges, Group 2

GWN03J90 GWN03K3R GWN03K6J GWN03K7T GWN03KR2 GWN03KR5 GWN03KRA GWN03KRD GWN03M89 GWN03M8D GWN03M8F GWN03NHT GWN03R73 GWN03R75 GWN03R77 GWN03R79 GWN03R7A GWN03R7C GWN03R7D GWN03R7G GWN03R7H GWN03R9J GWN03R9K GWN03R9L GWN03R9N GWN03R9R GWN03R9W GWN03RA0 GWN03RA1 GWN03RA4 GWN03RA6 GWN03RA7 GWN03RP7 GWN03RP9 GWN03RPE GWN03RPF GWN03RPG GWN04027 GWN04028 GWN04029 GWN0402E GWN0402G GWN0402H GWN0402J GWN0402K GWN0402M GWN0402N GWN0402P GWN0418C GWN0418G GWN0418K GWN0418M GWN0418P GWN0418T GWN0418W GWN04190 GWN04191 GWN0454E GWN0454F GWN0454G GWN0454J GWN0454K GWN0454L GWN045T1 GWN045T3 GWN045T4 GWN045T5 GWN045T6 GWN045T7 GWN045T9 GWN045TA GWN045TC GWN045TE GWN045TF GWN045TH GWN046F6 GWN046F7 GWN046F8 GWN04726 GWN047LG GWN047LH GWN047LJ GWN047LL GWN048CG GWN048CM GWN048CN GWN048CP GWN048CR GWN049GH GWN049GK GWN049JL GWN049JM GWN049M7 GWN04AEP GWN04AET GWN04ALT GWN04ALW GWN04AM0 GWN04AM2 GWN04AM3 GWN04AM4 GWN04CGL GWN04CHA GWN04CHC GWN04D55 GWN04DR4 GWN04DR9 GWN04DRE GWN04DRJ GWN04E9N GWN04EM5 GWN04F8N GWN04F8P GWN04FTJ

(3) Visually inspect the rotor disks for the presence of a chamfer on the aft breakedges of the dovetail slot bottoms. Use paragraph 3.A. of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to do the inspection.

(4) For disks that have the chamfered breakedges, re-mark, FPI, and ECI the rotor disk. Use paragraph 3.A.(2) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to re-mark and inspect the rotor disk, and remove from service as necessary.

(5) For disks that do not have the chamfered breakedges, remove the disk from service. Use paragraph 3.A.(4) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006.

CF6-80C2 Series Engines

Stage 1 HPT Rotor Disks, P/N 1531M84G12, With Chamfered Breakedges

(k) For stage 1 HPT rotor disks, P/N 1531M84G12, with SNs listed in Table 6B of this AD, with chamfered breakedges:

(1) With more than 6,900 CSN, perform paragraph (k)(3) at the next ESV, but not to exceed 500 cycles after the effective date of this AD.

(2) With 6,900 CSN or fewer, perform paragraph (k)(3) at the next ESV, but before accumulating 7,400 CSN.

[[Page 47723]]

Table 6B.--SNs of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1531M84G12, With Chamfered Breakedges

GWN04CH6 GWN04G5H GWN04M03

(3) FPI and ECI the rotor disk. Use paragraph 3.A.(3) of the Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1217, dated July 20, 2006, to re-mark and inspect the rotor disk, and remove from service as necessary.

Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 with SNs not listed in Table 6 and Table 6A of this AD

(l) For stage 1 HPT rotor disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 with SNs not listed in Table 6 and Table 6A of this AD, inspect, rework, and re-mark the disks using paragraphs 3.A.(1) through 3.A.(2) of Accomplishment Instructions of GE SB No. CF6-80C2 S/B 72-1089, Revision 3, dated July 20, 2006, at the following, unless already done using superseded AD 2004-04-07:

(1) For both new and used stage 1 HPT rotor disks not installed in engines, inspect, rework, re-mark, and remove from service as necessary before further flight.

(2) For stage 1 HPT rotor disks that have been inspected before March 12, 2004 (effective date of superseded AD 2004-04-07) using GE ASB No. CF6-80C2 S/B 72-A1024, Revision 1, dated November 3, 2000, or any version of GE ASB No. CF6-80C2 S/B 72-A1026, inspect, rework, re-mark, and remove from service as necessary using the compliance times in the following Table 7:

Table 7.--Compliance Times for Inspection and Rework of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 With SNs Not Listed in Table 6 and Table 6A of This AD--Previously Inspected

Stage 1 HPT rotor disk cycles-since- last-inspection (CSLI) on March 12, Compliance time for inspection 2004 (effective date of superseded AD

and rework 2004-04-07)

(i) More than 1,500 CSLI............... At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 4,500 CSLI. (ii) 1,500 CSLI or fewer............... At the next ESV after March 12, 2004 (effective date of superseded AD 2004-04-07), but not to exceed 3,500 CSLI.

(3) For stage 1 HPT rotor disks that have not been inspected before March 12, 2004 (effective date of superseded AD 2004-04-07) using GE ASB No. CF6-80C2 S/B 72-A1024, Revision 1, dated November 3, 2000, or any version of GE ASB No. CF6-80C2 S/B 72-A1026, inspect, rework, re-mark, and remove from service as necessary using the following Table 8 or Table 8A compliance times, whichever occurs first:

Table 8.--Compliance Times for Inspection and Rework of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 With SNs Not Listed in Table 6 and Table 6A of This AD--Not Previously Inspected

Stage 1 HPT rotor disk cycles-since-new Compliance time for inspection (CSN) on the effective date of this AD

and rework

(i) 9,000 or more CSN.................. Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first. (ii) 6,900 or more but fewer than 9,000 Within 500 CIS after the CSN.

effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first. (iii) Fewer than 6,900 CSN............. Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first.

Table 8A.--Compliance Times for Inspection and Rework of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/Ns 9392M23G10, G12, G21, 1531M84G02, G06, G08, and 1531M84G10 With SNs Not Listed in Table 6 and Table 6A of This AD--Not Previously Inspected

Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD Compliance time for inspection 2004-04-07)

and rework

(i) 10,000 or more CSN................. At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first. (ii) 5,000 or more CSN but fewer than At the next ESV or within 2,400 10,000 CSN.

CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), but before accumulating 11,000 CSN. (iii) Fewer than 5,000 CSN............. At the next ESV or within 3,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 7,400 CSN.

Stage 1 HPT Rotor Disks, P/N 1862M23G01

(m) For stage 1 HPT rotor disk, P/N 1862M23G01, remove the disk from service at the following times:

(1) For stage 1 HPT rotor disks not installed in engines, remove from service as necessary before further flight.

(2) For stage 1 HPT rotor disks that have been inspected before March 12, 2004 (effective date of superseded AD 2004-04-07), using any version of GE ASB No. CF6-80C2 S/B 72-A1026, and had more than zero CSN at the time of that inspection, remove from service at next ESV.

(3) For stage 1 HPT rotor disks that have not been inspected, or were only inspected with zero CSN before March 12, 2004 (effective date of superseded AD 2004-04-07), using any version of GE ASB No. CF6-80C2 S/B 72-A1026, remove from service

[[Page 47724]]

using the following Table 9 or Table 9A compliance times, whichever occurs first:

Table 9.--Compliance Times for Removal of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1862M23G01--Not Previously Inspected

Stage 1 HPT rotor disk CSN on the effective date of this AD

Compliance time for removal

(i) 9,000 or more CSN.................. Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first. (ii) 6,900 or more but fewer than 9,000 Within 500 CIS after the CSN.

effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first. (iii) Fewer than 6,900 CSN............. Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first.

Table 9A.--Compliance Times for Removal of CF6-80C2 Series Stage 1 HPT Rotor Disks, P/N 1862M23G01--Not Previously Inspected

Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of superseded AD Compliance time for removal 2004-04-07)

(i) 10,000 or more CSN................. At the next ESV or within 1,000 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first. (ii) 5,000 or more CSN but fewer than At the next ESV or within 2,400 10,000 CSN.

CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 11,000 CSN. (iii) Fewer than 5,000 CSN............. At the next ESV or within 3,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 7,400 CSN.

CF6-80E1A2, A4 Engines

Stage 1 HPT Rotor Disks, P/N 1639M41P04

(n) For stage 1 HPT rotor disks, P/N 1639M41P04, remove the rotor disks from service using paragraphs 3.A.(1) through 3.A.(2) of Accomplishment Instructions of GE SB No. CF6-80E1 S/B 72-0251, dated January 22, 2004, at the following times:

(1) For stage 1 HPT rotor disks currently in service, remove the disk using the compliance times in the following Table 10 or Table 10A compliance times, whichever occurs first:

Table 10.--Compliance Times for Removal of CF6-80E1 Stage 1 HPT Rotor Disks, P/N 1639M41P04

Stage 1 HPT rotor disk CSN on the effective date of this AD

Compliance Time For Removal

(i) 9,000 or more CSN.................. Within 250 CIS after the effective date of this AD, or by March 31, 2007, whichever occurs first. (ii) 6,900 or more but fewer than 9,000 Within 500 CIS after the CSN.

effective date of this AD, but before accumulating 9,250 CSN, or by December 31, 2007, whichever occurs first. (iii) Fewer than 6,900 CSN............. Before accumulating 7,400 CSN, or by December 31, 2008, whichever occurs first.

Table 10A.--Compliance Times for Removal of CF6-80E1 Stage 1 HPT Rotor Disks, P/N 1639M41P04

Stage 1 HPT rotor disk CSN on the March 12, 2004 ( effective date of superseded Compliance time for removal AD 2004-04-07)

(i) More than 10,000 CSN............... At the next ESV or within 600 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first. (ii) More than 5,000 CSN but fewer than At the next ESV or within 2,500 or equal to 10,000 CSN.

CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 10,600 CSN. (iii) Fewer than or equal to 5,000 CSN. At the next ESV or within 3,500 CIS after March 12, 2004 (effective date of superseded AD 2004-04-07), whichever occurs first, but before accumulating 7,500 CSN.

(2) After March 12, 2004 (effective date of superseded AD 2004- 04-07), do not install any stage 1 HPT rotor disk, P/N 1639M41P04, into any engine.

Definitions

(o) For the purpose of this AD, the following definitions apply:

(1) An engine shop visit (ESV) is when the engine is removed from an aircraft for maintenance and a major engine flange is disassembled. For stage 1 HPT rotor disks that have been inspected using any version of GE SB No. CF6-80A SB 72-0779 or any version of GE ASB No. CF6-80C2 ASB 72-A1026 or GE SB No. CF6-80C2 SB 72-A1024, Revision 1, dated November 3, 2000 or are listed in Table 6A or Table 6B, the following actions, either separately or in combination with each other, are not considered ESVs for the purpose of this AD:

(i) The removal of the upper compressor stator case solely for airfoil maintenance.

(ii) The module level inspection of the high-pressure compressor rotor 3-9 spool.

[[Page 47725]]

(iii) The replacement of stage 5 high-pressure compressor variable stator vane bushings or lever arms.

(2) Piece-part exposure is when according to the manufacturer's engine manual or other FAA-approved engine manual the stage 1 HPT rotor disk is considered completely disassembled.

Reporting Requirements

(p) Within five calendar days of the inspection, report the results of inspections that equal or exceed the reject criteria to: Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7176; fax (781) 238-7199. Reporting requirements have been approved by the Office of Management and Budget and assigned OMB control number 2120-0056. Be sure to include the following information:

(1) Engine model in which the stage 1 HPT rotor disk was installed.

(2) Part Number.

(3) Serial Number.

(4) Part CSN.

(5) Part CSLI.

(6) Date and location where inspection was done.

(q) We request that you record the inspection information and results on GE Form 1653-1, entitled CF6-80A/80C Stage 1 HPT Disk Dovetail Slot Bottom Inspection. This form is available in any version of GE SB CF6-80A S/B 72-0779, or GE ASB CF6-80C2 S/B 72- A1026. We also request that a copy of the data be sent to GE Airline Support Engineering, General Electric Aircraft Engines, Customer Support Center, 1 Neumann Way, Mail Drop RM285, Cincinnati, OH 45215.

Alternative Methods of Compliance

(r) 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.

Material Incorporated by Reference

(s) You must use the service information specified in Table 11 to perform the actions required by this AD. The Director of the Federal Register previously approved the incorporation by reference of General Electric Service Bulletins No. CF6-80E1 S/B 72-0251, dated January 22, 2004 and No. CF6-80A S/B 72-0779, Revision 1, dated January 22, 2004, and Alert Service Bulletin No. CF6-80C2 S/B 72-A1026, Revision 2, dated January 22, 2004, as of March 12, 2004 (69 FR 8801, February 26, 2004). The Director of the Federal Register approved the incorporation by reference of the other documents listed in Table 11 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672-8400, fax (513) 672-8422. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, Suite 700, Washington, DC. Table 11 follows:

Table 11.--Incorporation by Reference

Service Bulletin No.

Page

Revision

Date

GE SB No. CF6-80E1 S/B 72-0251... All.................. Original............. January 22, 2004.

Total Pages: 4 GE SB No. CF6-80A S/B 72-0779.... ALL.................. 1.................... January 22, 2004.

Total Pages: 34 GE SB No. CF6-80A S/B 72-0788.... ALL.................. 3.................... July 20, 2006.

Total Pages: 11 GE ASB No. CF6-80C2 S/B 72-A1026. ALL.................. 2.................... January 22, 2004.

Total Pages: 38 GE SB No. CF6-80C2 S/B 72-1089... ALL.................. 3.................... July 20, 2006.

Total Pages: 11 GE SB No. CF6-80C2 S/B 72-1217... ALL.................. Original............. July 20, 2006.

Total Pages: 12 GE SB No. CF6-80A S/B 72-0822.... ALL.................. Original............. July 20, 2006.

Total Pages: 10

Related Information

(t) GE ASB No. CF6-80C2 S/B 72-A1024, Revision 1, dated November 3, 2000 also pertains to the subject of this AD.

Issued in Burlington, Massachusetts, on August 10, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-13437 Filed 8-17-06; 8:45 am]

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