AD 91-15-25

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 thecompliance 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 1-80if 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.