AD 91-15-25
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CF6-80A | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80A1 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80A2 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80A3 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2A1 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2A2 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2A3 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2A5 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2A8 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B1 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B1F | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B1F1 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B2 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B2F | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B4 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B4F | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B6 | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2B6F | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
| engine | General Electric Company | CF6-80C2D1F | GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines |
Unsafe Condition
Vane to spool rub damage on high pressure compressor rotor (HPCR) stages 11-14 spool-shafts could cause an uncontained engine failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect HPCR stages 11-14 spool-shafts for vane to spool rubs using specified service bulletins. Remove from service spool-shafts with rub damage within 500 cycles in service after the AD effective date or prior to 8,000 cycles since new, whichever is later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 500 cycles in service (CIS) after the effective date of this AD, or prior to accumulating 8000 cycles since new, whichever occurs later
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
GE CF6-80A series (S/N 580-101 through 580-319, 585-101 through 585-222) and CF6-80C2 series engines (S/N 690-101 through 690-181, 695-101 through 695-150, 705-101 through 705-112) with specified part numbers installed on Airbus A300, A310, Boeing 747, and 767 aircraft.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
High Pressure Compressor Rotor
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_91-15-25.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 91-15-25 Document Type: AD Final Rules Docket Number: 90-ANE-34 Subject Heading: GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines Subject: High Pressure Compressor Rotor Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/06/1991 Make: General Electric Company Model: CF6-80A | CF6-80A1 | CF6-80A2 | CF6-80A3 | CF6-80C2A1 | CF6-80C2A2 | CF6-80C2A3 | CF6-80C2A5 | CF6-8...Show more Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 91-15-25 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-ANE-34 AMENDMENT: 39-7090 AD NUMBER: 91-15-25 SUBJECT HEADING: GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines ACTION: SUMMARY: DATES: Effective September 6, 1991. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 91-15-25 GENERAL ELECTRIC COMPANY (GE): Amendment 39-7090. Docket No. 90- ANE-34. Applicability: GE CF6-80A series and CF6-80C2 series engines, installed on, but not limited to, Airbus A300 and A310 and Boeing 747 and 767 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent an uncontained engine failure, accomplish the following: (a) Inspect high pressure compressor rotor (HPCR) stages 11-14 spool-shafts for vane to spool rubs within 500 cycles in service (CIS) after the effective date of this AD, or prior to accumulating 8000 cycles since new, whichever occurs later, according to the following: (1) Inspect CF6-80A series engines, Serial Numbers (S/N) 580-101 through 580-319, and S/N 585-101 through 585-222, installed with an HPCR stages 11-14 spool-shaft, Part Number (P/N) 9225M37G11, 9225M37G14, 9225M37G16, 9225M37G19, 9225M37G20, or 9225M37G21, in accordance with the Accomplishment Instructions in GE CF6-80A Service Bulletin (SB) 72-459, Revision 2, dated June 14, 1989. (2) Inspect CF6-80C2 series engines, S/N 690-101 through 690-181, S/N 695-101 through 695-150, and S/N 705-101 through 705-112, installed with an HPCR stages 11- 14 spool-shafts, P/N 9380M30G07, 9380M30G08, 9380M30G09, 9380M30G10, or 1531M21G01, in accordance with the Accomplishment Instructions in GE CF6-80C2 SB 72-130, Revision 2, dated October 18, 1989. (3) Inspect in accordance with the applicable requirements of paragraph (a)(1) or (a)(2) of this AD, HPCR stages 11-14 spool-shafts which were installed in a high pressure compressor (HPC) at an engine shop visit, with stages 10 through 13 vane radiiless than the values indicated in Table 1 of this AD for CF6-80A service engines, and Table 2 of this AD for CF6-80C2 series engines. (b) The inspection requirements of paragraph (a) of this AD are not applicable to HPCR stages 11-14 spool-shafts visually inspected at the piece-part level, determined not to have vane to spool rub damage, and were installed in an HPC with stages 10 through 13 vane radii greater than or equal to the values indicated in Table 1 of this AD for CF6-80A series engines, and Table 2 of this AD for CF6-80C2 series engines. (c) Remove from service within 500 CIS after the effective date of this AD or prior to accumulating 8,000 cycles since new, whichever occurs later, HPCR stages 11-14 spool-shafts with vane to spool rub damage. NOTE: CF6-80A SB 72-460 and CF6-80C2 SB 72-131 introduce an FAA approved rework procedure to increase the FAA approved life limit for HPCR stages 11-14 spool-shafts with vane to spool rub damage. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (f) The inspections shall be done in accordance with the following GE documents: DOCUMENT PAGE NO. ISSUE/REVISION DATE GE CF6-80A 2-9 Original 11/25/86 SB 72-459 1 Rev. 2 6/14/89 Total Pages: 9 GE CF6-80C2 2-9 Original 11/25/86 SB 72-130 1 Rev. 2 10/18/89 Total Pages: 9 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. TABLE 1 CF6-80A HPC Stator Vane Minimum Radii Vane Stage Position Minimum Vane Radius (in) Stage 10 Vanes 1-6, 35-80 11.416 7-8, 33, 34 11.417 9, 10, 31, 32 11.418 11, 12, 29, 30 11.419 13-16, 25-28 11.420 17-24 (or 1-80 if round grind) 11.421 Stage 11 Vanes 1-6, 35-80 11.623 7, 8, 33, 34 11.624 9, 10, 31, 32 11.625 11, 12, 29, 30 11.626 13, 16, 25-28 11.627 17-24 (or 1-80 11.628 if round grind) Stage 12 Vanes with Liners 1-10, 31-80 11.769 11, 12, 29, 30 11.770 13-15, 26-28 11.771 16-25 (or 1-80 if round grind) 11.772 Stage 12 Vanes without Liners 1-10, 31-80 11.786 11, 12, 29, 30 11.787 13-15, 26-28 11.788 16-25 (or 1-80 if round grind) 11.789 Stage 13 Vanes 1-10, 31-80 11.903 11, 12, 29, 30 11.904 13-15, 26-28 11.905 16-25 (or 1-80 if round grind) 11.906 NOTES: (1) Vane radius is measured from vane tip at vane centerline to stator case centerline. (2) Vane positions are numbered clockwise, aft looking forward, starting with No. 1 at the left hand horizontal split line upper stator case. (3) These revised minimum vane radii were incorporated into the CF6-80A Engine Manual, GEK 72501, in Revision 23. TABLE 2 CF6-80C2 HPC Stator Vane Minimum Radii Vane Stage Position Minimum Vane Radius (in) Stage 10 Vanes 1-6, 35-80 11.409 7, 34 11.410 8, 9, 32, 33 11.411 10, 31 11.412 11, 12, 29, 30 11.413 13, 14, 27, 28 11.414 15, 16, 25, 26 11.415 17-24 (or 1-80 if round grind) 11.416 Stage 11 Vanes 1-6, 35-80 11.617 7, 34 11.618 8, 9, 32, 33 11.619 10, 31 11.620 11, 12, 29, 30 11.621 13, 14, 27, 28 11.622 15, 16, 25, 26 11.623 17-24 (or 1-80 if round grind) 11.624 Stage 12 Vanes 1-10, 32-84 11.780 11, 31 11.781 12, 13, 29, 30 11.782 14-16, 26-28 11.783 17-25 (or 1-84 if round grind) 11.784 Stage 13 Vanes 1-10, 31-80 11.906 11, 12, 29, 30 11.907 13, 14, 27, 28 11.908 15, 16, 25, 26 11.909 17-24 (or 1-80 if round grind) 11.910 NOTES: (1) Vane radius is measured from vane tip at vane centerline to stator case centerline. (2) Vane positions are numbered clockwise, aft looking forward, starting with No. 1 at the left hand horizontal split line upper stator case. (3) These revised minimum vane radii were incorporated into the CF6-80C2 Engine Manual, GEK 92451, in Revision 7. This amendment (39-7090, AD 91-15-25) becomes effective on September 6, 1991. FOOTER:
Document Text
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AD Final Rules - DRS_91-15-25.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 91-15-25 Document Type: AD Final Rules Docket Number: 90-ANE-34 Subject Heading: GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines Subject: High Pressure Compressor Rotor Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/06/1991 Make: General Electric Company Model: CF6-80A | CF6-80A1 | CF6-80A2 | CF6-80A3 | CF6-80C2A1 | CF6-80C2A2 | CF6-80C2A3 | CF6-80C2A5 | CF6-8...Show more Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 91-15-25 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 90-ANE-34 AMENDMENT: 39-7090 AD NUMBER: 91-15-25 SUBJECT HEADING: GENERAL ELECTRIC COMPANY (GE) Models GE CF6-80A series and CF6-80C2 series engines ACTION: SUMMARY: DATES: Effective September 6, 1991. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 91-15-25 GENERAL ELECTRIC COMPANY (GE): Amendment 39-7090. Docket No. 90- ANE-34. Applicability: GE CF6-80A series and CF6-80C2 series engines, installed on, but not limited to, Airbus A300 and A310 and Boeing 747 and 767 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent an uncontained engine failure, accomplish the following: (a) Inspect high pressure compressor rotor (HPCR) stages 11-14 spool-shafts for vane to spool rubs within 500 cycles in service (CIS) after the effective date of this AD, or prior to accumulating 8000 cycles since new, whichever occurs later, according to the following: (1) Inspect CF6-80A series engines, Serial Numbers (S/N) 580-101 through 580-319, and S/N 585-101 through 585-222, installed with an HPCR stages 11-14 spool-shaft, Part Number (P/N) 9225M37G11, 9225M37G14, 9225M37G16, 9225M37G19, 9225M37G20, or 9225M37G21, in accordance with the Accomplishment Instructions in GE CF6-80A Service Bulletin (SB) 72-459, Revision 2, dated June 14, 1989. (2) Inspect CF6-80C2 series engines, S/N 690-101 through 690-181, S/N 695-101 through 695-150, and S/N 705-101 through 705-112, installed with an HPCR stages 11- 14 spool-shafts, P/N 9380M30G07, 9380M30G08, 9380M30G09, 9380M30G10, or 1531M21G01, in accordance with the Accomplishment Instructions in GE CF6-80C2 SB 72-130, Revision 2, dated October 18, 1989. (3) Inspect in accordance with the applicable requirements of paragraph (a)(1) or (a)(2) of this AD, HPCR stages 11-14 spool-shafts which were installed in a high pressure compressor (HPC) at an engine shop visit, with stages 10 through 13 vane radiiless than the values indicated in Table 1 of this AD for CF6-80A service engines, and Table 2 of this AD for CF6-80C2 series engines. (b) The inspection requirements of paragraph (a) of this AD are not applicable to HPCR stages 11-14 spool-shafts visually inspected at the piece-part level, determined not to have vane to spool rub damage, and were installed in an HPC with stages 10 through 13 vane radii greater than or equal to the values indicated in Table 1 of this AD for CF6-80A series engines, and Table 2 of this AD for CF6-80C2 series engines. (c) Remove from service within 500 CIS after the effective date of this AD or prior to accumulating 8,000 cycles since new, whichever occurs later, HPCR stages 11-14 spool-shafts with vane to spool rub damage. NOTE: CF6-80A SB 72-460 and CF6-80C2 SB 72-131 introduce an FAA approved rework procedure to increase the FAA approved life limit for HPCR stages 11-14 spool-shafts with vane to spool rub damage. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (f) The inspections shall be done in accordance with the following GE documents: DOCUMENT PAGE NO. ISSUE/REVISION DATE GE CF6-80A 2-9 Original 11/25/86 SB 72-459 1 Rev. 2 6/14/89 Total Pages: 9 GE CF6-80C2 2-9 Original 11/25/86 SB 72-130 1 Rev. 2 10/18/89 Total Pages: 9 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. TABLE 1 CF6-80A HPC Stator Vane Minimum Radii Vane Stage Position Minimum Vane Radius (in) Stage 10 Vanes 1-6, 35-80 11.416 7-8, 33, 34 11.417 9, 10, 31, 32 11.418 11, 12, 29, 30 11.419 13-16, 25-28 11.420 17-24 (or 1-80 if round grind) 11.421 Stage 11 Vanes 1-6, 35-80 11.623 7, 8, 33, 34 11.624 9, 10, 31, 32 11.625 11, 12, 29, 30 11.626 13, 16, 25-28 11.627 17-24 (or 1-80 11.628 if round grind) Stage 12 Vanes with Liners 1-10, 31-80 11.769 11, 12, 29, 30 11.770 13-15, 26-28 11.771 16-25 (or 1-80 if round grind) 11.772 Stage 12 Vanes without Liners 1-10, 31-80 11.786 11, 12, 29, 30 11.787 13-15, 26-28 11.788 16-25 (or 1-80 if round grind) 11.789 Stage 13 Vanes 1-10, 31-80 11.903 11, 12, 29, 30 11.904 13-15, 26-28 11.905 16-25 (or 1-80 if round grind) 11.906 NOTES: (1) Vane radius is measured from vane tip at vane centerline to stator case centerline. (2) Vane positions are numbered clockwise, aft looking forward, starting with No. 1 at the left hand horizontal split line upper stator case. (3) These revised minimum vane radii were incorporated into the CF6-80A Engine Manual, GEK 72501, in Revision 23. TABLE 2 CF6-80C2 HPC Stator Vane Minimum Radii Vane Stage Position Minimum Vane Radius (in) Stage 10 Vanes 1-6, 35-80 11.409 7, 34 11.410 8, 9, 32, 33 11.411 10, 31 11.412 11, 12, 29, 30 11.413 13, 14, 27, 28 11.414 15, 16, 25, 26 11.415 17-24 (or 1-80 if round grind) 11.416 Stage 11 Vanes 1-6, 35-80 11.617 7, 34 11.618 8, 9, 32, 33 11.619 10, 31 11.620 11, 12, 29, 30 11.621 13, 14, 27, 28 11.622 15, 16, 25, 26 11.623 17-24 (or 1-80 if round grind) 11.624 Stage 12 Vanes 1-10, 32-84 11.780 11, 31 11.781 12, 13, 29, 30 11.782 14-16, 26-28 11.783 17-25 (or 1-84 if round grind) 11.784 Stage 13 Vanes 1-10, 31-80 11.906 11, 12, 29, 30 11.907 13, 14, 27, 28 11.908 15, 16, 25, 26 11.909 17-24 (or 1-80 if round grind) 11.910 NOTES: (1) Vane radius is measured from vane tip at vane centerline to stator case centerline. (2) Vane positions are numbered clockwise, aft looking forward, starting with No. 1 at the left hand horizontal split line upper stator case. (3) These revised minimum vane radii were incorporated into the CF6-80C2 Engine Manual, GEK 92451, in Revision 7. This amendment (39-7090, AD 91-15-25) becomes effective on September 6, 1991. FOOTER:
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