# [Amended]
**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: *[email protected].*
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.
**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.
**14 CFR Part 39**
**Adoption of the Amendment**
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**
1. The authority citation for part 39 continues to read as follows:
**Authority:**
49 U.S.C. 106(g), 40113, 44701.
§ 39.13
**14 CFR Part 39**
2. The FAA amends § 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:
| Models | Stage 1 high pressure turbine (HPT) rotor disk part numbers (P/Ns) | Engines installed on but not limited to |
| --- | --- | --- |
| CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3 | 9234M67G22/G24/G25/G26, 9362M58G02/G06/G07/G09, 9367M45G02/G04/G09 | Airbus A310 and Boeing 767 airplanes. |
| CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A8, CF6-80C2A5F, CF6-80C2B1, CF6-80C2B2, CF6-80C2B4, CF6-80C2B6, CF6-80C2B1F, CF6-80C2B2F, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2D1F | 1862M23G01, 9392M23G10/G12/G21, 1531M84G02/G06/G08/G10/G12 | Airbus A300, A310, Boeing 747, 767, and McDonnell Douglas MD11 airplanes. |
| 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 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:
| |
| --- |
| 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:
| Stage 1 HPT rotor disk cycles-since-last-inspection (CSLI) on March 12, 2004 (effective date of superseded AD 2004-04-07) | Compliance time for inspection and rework |
| --- | --- |
| (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:
| Stage 1 HPT rotor disk cycles-since-new (CSN) on the effective date of this AD | Compliance time for inspection 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 CSN | Within 500 CIS after the 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. |
| Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of | Compliance time for inspection 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 10,000 CSN | At the next ESV or within 2,400 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:
| 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 CSN | Within 500 CIS after the 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. |
| Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of | Compliance time for removal |
| --- | --- |
| (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 10,000 CSN | At the next ESV or within 2,400 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:
| |
| --- |
| 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 |
| 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 |
| 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.
| |
| --- |
| 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.
| |
| --- |
| 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:
| Stage 1 HPT rotor disk cycles-since-last-inspection (CSLI) on March 12, 2004 (effective date of superseded AD 2004-04-07) | Compliance time for inspection and rework |
| --- | --- |
| (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:
| Stage 1 HPT rotor disk cycles-since-new (CSN) on the effective date of this AD | Compliance time for inspection 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 CSN | Within 500 CIS after the 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. |
| Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of | Compliance time for inspection 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 10,000 CSN | At the next ESV or within 2,400 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 using the following Table 9 or Table 9A compliance times, whichever occurs first:
| 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 CSN | Within 500 CIS after the 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. |
| Stage 1 HPT rotor disk CSN on March 12, 2004 (effective date of | Compliance time for removal |
| --- | --- |
| (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 10,000 CSN | At the next ESV or within 2,400 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:
| 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 CSN | Within 500 CIS after the 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. |
| Stage 1 HPT rotor disk CSN on the March 12, 2004 ( effective date of superseded AD 2004-04-07) | Compliance time for removal |
| --- | --- |
| (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 or equal to 10,000 CSN | At the next ESV or within 2,500 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.
(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:
| 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.