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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 1 of 37 TRANSMITTAL INFORMATION CF6-80C2 Service Bulletin 72-0222 Revision 4 This section transmits Revision 4 to CF6-80C2 S/B 72-0222, dated April 26, 1988. Revision 1 was dated March 21. 1989. All pages were not included. Revision 2 was dated May 10, 1990. All pages were not included. Revision 3 was dated August 31, 1999. All pages were not included. This revision is issued to correct the configuration chart to identify mounting platform 1292M13G05 for Boeing applications only. Also, the CF6-80C2B1F engine model is added. Engines that have previously complied with this Service Bulletin are not affected. Technical content of this Service Bulletin is FAA approved. The revision bars in the left margin identify changes. This Service Bulletin is reissued in its entirety. GEAE Distribution Code: 853 1. PLANNING INFORMATION A. Effectivity CF6-80C2A1/A2/A3/B1/B2/B4/B1F (1) The following parts installed on CF6-80C2 engines or stocked as spare parts are affected by this Service Bulletin: Description Part number Engine Model (Series) Yoke, Engine Mount 9383M43G10 A / B Link, Platform 9383M42G03 A / B 9383M42G04 A / B Link, Frame 9383M45G01 A / B 9383M45G02 A / B Bolt, Hex Head 9383M54P01 A / B 9395M30P04 A / B Bushing, Flanged 9383M49P04 A / B 9383M49P17 A / B

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 2 Description Part number Engine Model (Series) Bushing, Flanged 9383M49P18 A / B 9383M49P19 A / B 9383M49P12 A / B 9383M49P26 A / B 9383M49P27 A / B 9383M49P28 A / B 9383M49P01 A / B 9383M49P14 A / B 9383M49P15 A / B 9383M49P16 A / B Spacer 1288M88P02 A / B Retainer, Bolt 9383M57P001A A / B 9383M60P003A A / B 1288M87P001A A / B Plate, Lock 9383M58P001A A / B 9383M61P001A A / B 9383M61P003A A / B Frame, Fan 9382M37G47 A / B Assembly, Platform 1301M28G04/G05/G06 A Mount, Engine 1292M13G04/G05 B (2) The improvements described in this Service Bulletin will be introduced into production on CF6-80C2A/B series engines, S/N 690-191, -193 through -197, -199 and up (GE-Assembled), S/N 695-165 and up (SNECMA-assembled) NOTE: The above engine introduction points/effectivities are based on production forecast information and should be used by the recipient of this Service Bulletin for planning purposes only. B. Concurrent Requirements
None. C. Description This Service Bulletin introduces a redesigned forward engine thrust mount system and provides instructions for installing the new system. Instructions are also provided for reworking the fan frame lugs, yoke assembly, and platforms to accept the new bearings and larger bolts.

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 3 D. Compliance Category 3 This is a Campaign Change. It is recommended that this Service Bulletin be accomplished at the next shop visit consistent with the 5000-cycle limit on the thrust links and bolts. Continued applicable warranty coverage, as described in General Contract Terms and Agreements, is conditioned upon compliance with the recommendation and related accomplishment instructions specified in this Service Bulletin.
E. Reason This Service Bulletin introduces a redesigned forward engine thrust mount system, which increases the fatigue life of this system so that it is not life limited. On the old system the frame links, platform links, and shear bolts were life limited to 5000-cycles (reference CF6-80C2 S/B A72-162). The new strengthened system with the following changes will not require replacement at a specific interval:

Frame and Platform Links The new links have added material at both ends around the new bearings Bolts All the bolts have a larger diameter Yoke Enlarged holes to accept the larger diameter bolts Platform Enlarged holes to accept the larger diameter bolts Fan Frame Enlarged holes in lugs to accept larger diameter bolts and added improved spherical bearings for longer life F. Approval The FAA has approved the technical content of this Service Bulletin. G. Manpower An estimated 32.0 man-hours per engine are required to accomplish this Service Bulletin. H. Weight and Balance Accomplishment of this Service Bulletin results in a weight increase of 7.9 lbs (3.6 kg) at engine station 200.00. I. References Commercial Engine Standard Practices Manual, GEK 9250 CF6-80C2 Engine Manual, GEK 92451 CF6-80C2A Series Illustrated Parts Catalog, GEK 92452-1 CF6-80C2B Series Illustrated Parts Catalog, GEK 92452-2

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 4 CF6-80C2B (FADEC) Series Illustrated Parts Catalog (IPC), GEK 92452-4 CF6-80C2 Component Maintenance Manual, 71-21-01, GEK 100769 CF6-80C2 Series S/B A72-162, Forward Engine Mount Thrust Link Life Limit CF6-80C2A Series S/B 72-107, General - Spare Parts Release for CF6-80C2 Engines CF6-80C2 Series S/B 72-207, Fan Frame - Forward Mount Vertical Link Bolt Reversal CF6-80C2 Series S/B 72-217, General - Engine Mount Yoke and Mount Platform Improvement CF6-80C2 Series S/B 72-284, Fan Frame - Introduction of Uninstrumented Fan Frame NOTE: The reference documents listed below are for the engine manufacturer’s internal use only: CID: 191493, -1, -2,192337, 192508, 192115, 192494, 192490, 193058 J. Publications Affected CF6-80C2A Series Illustrated Parts Catalog, GEK 92452-1 CF6-80C2B Series Illustrated Parts Catalog, GEK 92452-2 CF6-80C2B (FADEC) Series Illustrated Parts Catalog (IPC), GEK 92452-4 K. Interchangeability Individually, the old and new parts are not physically interchangeable. The new mount system must be introduced as a complete package. Intermix of new/old parts with new/old fan frames, yokes, and platforms is not permitted. Only the complete mounting system, which includes the fan frame, is physically interchangeable. 2. MATERIAL INFORMATION A. Material - Price and Availability (1) Parts necessary to do this Service Bulletin: Parts Necessary

Part Number Qty/ Eng Part Name Unit Price ($) Pkg Qty Lead time Days 1380M14G07 (1) Link, Platform See Note (1) 90 1380M14G08 (1) Link, Platform See Note (1) 90 1380M42G07 (1) Link, Frame See Note (1) 90 1380M42G08 (1) Link, Frame See Note (1) 90 1380M33P01 (4) Bolt, Shoulder 249.25 (1) 5

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 5

Part Number Qty/ Eng Part Name Unit Price ($) Pkg Qty Lead time Days
1380M34P01 (4) Bolt, Shoulder 200.00 (1) 20 1380M32P04 (2) Bushing, Flanged (Top) 150.75 (1) 5 1380M32P03 (2) Bushing, Flanged (Top) 150.75 (1) 5 1380M32P02 (2) Bushing, Flanged (Top) 150.75 (1) 5 1380M32P10 (2) Bushing, Flanged (Bottom) 150.75 (1) 5 1380M32P11 (2) Bushing, Flanged (Top) 152.50 (1) 5 1380M32P15 (2) Bushing, Flanged (Bottom) 152.50 (1) 5 1380M32P16 (2) Bushing, Flanged (Bottom) 152.50 (1) 5 1380M32P17 (2) Bushing, Flanged (Bottom) 150.75 (1) 5 MS14101-12C (3) Bearing * -- -- 1518M37P01 (AR) Bearing 271.75 (1) 7 1518M37P02 (ALT) Bearing 271.75 (1) 7 1518M37P03 (ALT) Bearing See Note (1) 60 1518M37P04 (ALT) Bearing See Note (1) 60 1518M37P05 (AR) Bearing See Note (1) 60 1518M37P06 (ALT) Bearing 271.75 (1) 7 1518M37P07 (ALT) Bearing See Note (1) 60 1518M37P08 (ALT) Bearing See Note (1) 60 1518M37P09 (AR) Bearing See Note (1) 60 1518M37P10 (ALT) Bearing See Note (1) 60 1518M37P11 (ALT) Bearing See Note (1) 60 1518M37P12 (ALT) Bearing See Note (1) 60 1518M37P13 (AR) Bearing See Note (1) 60 1518M37P14 (ALT) Bearing See Note (1) 60 1518M37P15 (ALT) Bearing See Note (1) 60 1518M37P16 (ALT) Bearing See Note (1) 60 1288M88P03 (2) Spacer 26.50 (10) 5 1537M26P001A (2) Retainer, Bolt See Note (1) 30

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 6

Part Number Qty/ Eng Part Name Unit Price ($) Pkg Qty Lead time Days 1537M28P001A (2) Retainer, Bolt See Note (1) 30 1288M87P003A (2) Retainer, Bolt See Note (1) 30 1537M25P001A (2) Plate, Lock See Note (1) 30 1537M29P001A (2) Plate, Lock See Note (1) 30 9383M61P005A (2) Plate, Lock See Note (1) 30 1537M24P001A (2) Bracket, Nut See Note (1) 30 1537M30P001A (2) Bracket, Nut See Note (1) 30 1537M27P001A (2) Bracket, Nut See Note (1) 30 9383M60P001A (2) Bolt, retainer See Note (1) 30 J626P05 (4) Nut See Note (25) 30 * GE Engine Services Distribution, L.L.C. does not sell these parts. NOTE: Refer to the IPC for the current part number. (2) Other spare parts: Other Spare Parts

Part Number Qty/ Eng Part Name Unit Price ($) Pkg Qty Lead time Days 9383M43G14 (1) Yoke Assembly, Engine Mount See Note (1) 90 1301M28G08 (1) Platform, Engine Mount (Airbus) See Note (1) 90 1292M13G06 (1) Platform, Engine Mount (Boeing) See Note (1) 90 9382M37G53 (1) Frame, Fan Quote -- -- 1380M32P12 (AR) Bushing, Flanged 150.75 (1) 5 1380M32P13 (AR) Bushing, Flanged 150.75 (1) 5 1380M32P14 (AR) Bushing, Flanged 150.75 (1) 5 NOTE: Refer to the IPC for the current part number.

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 7 (3) Consumables:
None. B. Industry Support Information (1) Manpower Support: A labor credit allowance of 32.0 man-hours will be given for each engine actually accomplished per the effectivity of this Service Bulletin. Submit a Warranty Claim to the following address to obtain this labor credit allowance: ATTN: CF6 Warranty/Guarantee Administration GE Aircraft Engines Product Support Operation One Neumann Way Room 444 Cincinnati, OH 45215-1988 USA Reference CF6-80C2 Series S/B 72-222 (2) Material Support: Material required to accomplish this Service Bulletin will be provided GE Engine Services Distribution, L.L.C. Reference paragraph 2.A., Material - Price and Availability. Send a Charge Purchase Order to: ATTN: Manager, Customer Account Support GE Engine Services Distribution, L.L.C. Product Support Operation One Neumann Way Room 115 Cincinnati, OH 45215-1988 USA A parts credit allowance will be provided under the terms of Campaign Change Warranty. To obtain this parts credit allowance, submit a Warranty Claim to the address in paragraph 2.B.(1), Manpower Support. Rotable yokes and platforms will be provided by GE on an allocated basis. Send a No-charge Purchase Order referencing CF6-80C2 S/B 72-222 to the address above.

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 8 C. Configuration Chart Configuration Chart

New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
9255M25G01 (X) Assembly, Engine CF6-80C2A Series 9255M25G01 (X) RM -/-
9255M70G01 (X) Assembly, Engine CF6-80C2B Series 9255M70G01 (X) RM -/-

9255M75G01 (X) Assembly, Engine CF6-80C2BF Series 9255M75G01 (X) RM -/-
.9383M43G14 (1) Yoke Assembly Engine Mount .9383M43G10 71-00-00-90A-445 (1) RE 3/A

OR OR .9383M43G13 (1) Yoke Assembly Engine Mount .9383M43G10 71-00-00-90A-445 (1) RE 3/A

.9383M43G10 * (S/B 72-222) (1) Yoke Assembly Engine Mount .9383M43G10 71-00-00-90A-445 (1) RW 3/-
..9383M41P03 (1) Yoke ..9383M41P01 71-00-00-90A-450 (1) RE 3/A

OR OR
..9383M41P01 * (S/B 72-222) (1) Yoke ..9383M41P01 71-00-00-90A-450 (1) RW 3/-
..MS14101-12-C (1) Bearing ..9204M99P02 71-00-00-90A-108 (1) RE 3/A
..1380M32P15 (2) Bushing, Flanged (Bottom) ..9383M49P08 71-00-00-90A-475 (2) RE 3/A
..1380M32P16 (2) Bushing, Flanged (Bottom) ..9383M49P13 71-00-00-90A-480 (2) RE 3/A
.1380M14G07 (1) Link, Platform .9383M42G03 71-00-00-90A-400 (1) RE 3/A

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 9 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
..1380M13P03 (1) Link ..9383M42P01 ** 72-00-00-45-280 (1) RE 3/A
..1531M49P01 (2) Bearing, Plain ..9383M50P01 71-00-00-90A-303 (2) RE 3/A
..1531M49P02 (Alt) Bearing, Plain ..9383M50P02 71-00-00-90A-303 (Alt) RE 3/A
..1531M49P03 (Alt) Bearing, Plain ..9383M50P03 71-00-00-90A-303 (Alt) RE 3/A
.9383M50P04 (Alt) Bearing, Plain ---------- (-) AD 5/- ---------- (-) Bearing, Plain ..9383M50P04 71-00-00-90A-403 (Alt) DE 5/A
---------- (-) Shim ..1304M86P01 71-00-00-90A-304 (1) DE 5/A
---------- (-) Shim ..1304M86P02 71-00-00-90A-305 (1) DE 5/A
.1380M14G08 (1) Link, Platform .9383M42G04 71-00-00-90A-300 (1) RE 3/A
..1380M13P04 (1) Link ..9383M42P02 72-00-00-45-302 (1) RE 3/A
..1531M49P01 (2) Bearing, Plain ..9383M50P01 71-00-00-90A-303 (1) RE 3/A
..1531M49P02 (Alt) Bearing, Plain ..9383M50P02 71-00-00-90A-303 (Alt) RE 3/A
..1531M49P03 (Alt) Bearing, Plain ..9383M50P03 71-00-00-90A-303 (Alt) RE 3/A
---------- (-) Shim ..1304M86P01 71-00-00-90A-304 (1) DE 5/A

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 10 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
---------- (-) Shim ..1304M86P02 71-00-00-90A-305 (1) DE 5/A
.1380M42G07 (1) Link, Frame .9383M45G01 71-00-00-90A-205 (1) RE 3/A
..1380M41P03 (1) Link ..9383M45P01 71-00-00-90A-207 (1) RE 3/A
..1531M15P01 (1) Bearing, Plain ..9204M99P02 71-00-00-90A-108 (1) RE 3/A
..1531M15P02 (Alt) Bearing, Plain ..9204M99P01 71-00-00-90A-108 (Alt) RE 3/A
..1531M15P03 (Alt) Bearing, Plain ..9204M99P09 71-00-00-90A-108 (Alt) RE 3/A
..1531M50P01 (1) Bearing, Plain ..9204M99P02 71-00-00-90A-108 (1) RE 3/A
..1531M50P02 (Alt) Bearing, Plain ..9204M99P01 71-00-00-90A-108 (Alt) RE 3/A
..1531M50P03 (Alt) Bearing, Plain ..9204M99P09 71-00-00-90A-108 (Alt) RE 3/A
.1380M42G08 (1) Link, Frame .9383M45G02 71-00-00-90A-105 (1) RE 3/A
..1380M41P04 (1) Link ..9383M45P02 71-00-00-90A-107 (1) RE 3/A
..1531M15P01 (1) Bearing, Plain ..9204M99P02 71-00-00-90A-108 (1) RE 3/A
..1531M15P02 (Alt) Bearing, Plain ..9204M99P01 71-00-00-90A-108 (Alt) RE 3/A
..1531M15P03 (Alt) Bearing, Plain ..9204M99P09 71-00-00-90A-108 (Alt) RE 3/A

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 11 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
..1531M50P01 (1) Bearing, Plain ..9204M99P02 71-00-00-90A-108 (1) RE 3/A
..1531M50P02 (Alt) Bearing, Plain ..9204M99P01 71-00-00-90A-108 (Alt) RE 3/A
..1531M50P03 (Alt) Bearing, Plain ..9204M99P09 71-00-00-90A-108 (Alt) RE 3/A
.1380M33P01 (4) Bolt, Shoulder .9383M54P01 71-00-00-90A-215 71-00-00-90A-260 71-00-00-90A-315 71-00-00-90A-360 (4) RE 3/A

.1380M34P01 (2) Bolt, Shoulder .9395M30P01 71-00-00-90A-065 71-00-00-90A-165 (2) RE 3/A

.1380M34P01 (2) Bolt, Shoulder .9395M30P04 ** 71-00-00-90A-010 71-00-00-90A-110 (2) RE 3/A

.1380M32P04 (2) Bushing, Flanged (Top) .9383M49P04 71-00-00-90A-550 (2) RE 3/A
------- (-) Bushing, Flanged .9383M49P17 71-00-00-90A-550 (AR) DE 5/A
------- (-) Bushing, Flanged .9383M49P18 71-00-00-90A-550 (AR) DE 5/A
------- (-) Bushing, Flanged .9383M49P19 71-00-00-90A-550 (AR) DE 5/A
.1380M32P03 (2) Bushing, Flanged (Top) .9383M49P12 71-00-00-90A-501 71-00-00-90A-510 (2) RE 3/A

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 12 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
------- (-) Bushing, Flanged .9383M49P26 71-00-00-90A-501 71-00-00-90A-510 (AR) DE 5/A

------- (-) Bushing, Flanged .9383M49P27 71-00-00-90A-501 71-00-00-90A-510 (AR) DE 5/A

------- (-) Bushing, Flanged .9383M49P28 71-00-00-90A-501 71-00-00-90A-510 (AR) DE 5/A

.1380M32P02 (2) Bushing, Flanged (Top) .9383M49P01 71-00-00-90A-496 71-00-00-90A-505 (1) RE 3/A

------- (-) Bushing, Flanged .9383M49P14 71-00-00-90A-496 71-00-00-90A-505 (AR) DE 5/A

------- (-) Bushing, Flanged .9383M49P15 71-00-00-90A-496 71-00-00-90A-505 (AR) DE 5/A

------- (-) Bushing, Flanged .9383M49P16 71-00-00-90A-496 71-00-00-90A-505 (AR) DE 5/A

.1288M88P03 (2) Spacer .1288M88P02 ** 71-00-00-90A-060 71-00-00-90A-160 (2) RE 3/A

.1380M32P01 (2) Bushing, Flanged ---------- (-) AD 5/- .1380M32P11 (AR) Bushing, Flanged (Top) .1380M32P01 ** 71-00-00-90A-020 71-00-00-90A-120 (2) RE 3/A

...1380M32P12 (AR) Bushing, Flanged ---------- (-) AD 5/-

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 13 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
...1380M32P13 (AR) Bushing, Flanged ---------- (-) AD 5/- ...1380M32P14 (AR) Bushing, Flanged ---------- (-) AD 5/- .1537M26P001A (2) Retainer, Bolt .9383M57P001A 71-00-00-90A-275 71-00-00-90A-375 (2) RE 3/A

.1537M25P001A (2) Plate, Lock .9383M58P001A 71-00-00-90A-265 71-00-00-90A-365 (2) RE 3/A

.1537M24P001A (2) Bracket, Nut .9383M58P001A 71-00-00-90A-265 71-00-00-90A-365 (2) RE 3/A

.1537M28P001A (2) Retainer, Bolt .9383M60P001A 71-00-00-90A-235 71-00-00-90A-335 (2) RE 3/A

.1537M29P001A (2) Plate, Lock .9383M61P001A 71-00-00-90A-220 71-00-00-90A-320 (2) RE 3/A

.1537M30P001A (2) Bracket, Nut . 9383M62P001A 71-00-00-90A-240 71-00-00-90A-340 (2) RE 3/A

.9383M60P001A (2) Retainer, Bolt .9383M60P003A 71-00-00-90A-085 71-00-00-90A-185 (2) RE 3/A

.9383M61P005A (2) Plate, Lock .9383M61P003A 71-00-00-90A-220 71-00-00-90A-320 (2) RE 3/A

.1537M27P001A (2) Bracket, Nut .9383M63P001A 71-00-00-90A-100 71-00-00-90A-200 (2) RE 3/A

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 14 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
.1288M87P003A (2) Retainer, Bolt .1288M87P001A ** 71-00-00-90A-055 71-00-00-90A-155 (2) RE 3/A

.9265M20G01/G02 (X) Module, Fan CF6-80C2 A/B .9265M20G01/ G02 (X) RM -/-

.9255M76G01 (X) Module, Fan CF6-80C2BF .9255M76G01 (X) RM -/-
..9382M37G53 (1) Frame, Fan ..9382M37G47 72-00-01-20-070 (1) RE/ RW 3/A

OR OR ..9382M37G46 * (S/B 72-222) (Alt) Frame, Fan ..9382M37G46 72-00-01-20-070 (Alt) RW 3/-

OR OR ..9382M37G48 * (S/B 72-222) (Alt) Frame, Fan ..9382M37G48 72-00-01-20-070 (Alt) RW 3/-
...MS14101-12C (2) Bearing ---------- (-) AD 5/- ...MS14101-12 (Alt) Bearing ---------- (-) AD 5/- ...1518M37P01 (AR) Bearing ---------- (-) AD 5/- ...1518M37P02 (AR) Bearing ---------- (-) AD 5/- ...1518M37P03 (AR) Bearing ---------- (-) AD 5/- ...1518M37P04 (AR) Bearing ---------- (-) AD 5/- ...1518M37P05 (AR) Bearing ---------- (-) AD 5/- ...1518M37P06 (AR) Bearing ---------- (-) AD 5/- ...1518M37P07 (AR) Bearing ---------- (-) AD 5/- ...1518M37P08 (AR) Bearing ---------- (-) AD 5/-

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 15 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
...1518M37P09 (AR) Bearing ---------- (-) AD 5/- ...1518M37P10 (AR) Bearing ---------- (-) AD 5/- ...1518M37P11 (AR) Bearing ---------- (-) AD 5/- ...1518M37P12 (AR) Bearing ---------- (-) AD 5/- ...1518M37P13 (AR) Bearing ---------- (-) AD 5/- ...1518M37P14 (AR) Bearing ---------- (-) AD 5/- ...1518M37P15 (AR) Bearing ---------- (-) AD 5/- ...1518M37P16 (AR) Bearing ---------- (-) AD 5/- ---------- (-) Bearing ...9204M99P01 thru P04 72-23-00-10-010 (AR) DE 5/A

...1380M32P10 (2) Bushing, Flanged (Bottom) ...1380M32P05 ** (2) RE 3/A
...1380M32P05 (Alt) Bushing, Flanged ----------- (-) AD 5/- ------- (-) Bushing, Flanged ...9383M49P03 ** 72-23-00-10-020 (AR) DE 5/A
------- (-) Bushing, Flanged ...9383M49P05 ** 72-23-00-10-021 (AR) DE 5/A
------- (-) Bushing, Flanged ...9383M49P06 ** 72-23-00-10-022 (AR) DE 5/A
------- (-) Bushing, Flanged ...9383M49P07 ** 72-23-00-10-023 (AR) DE 5/A
.683L163G01 (X) Kit, Front Mount Platform (CF6-80C2A) .683L163G01 (X) RM -/-

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 16 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code
..1301M28G08 (1) Platform, Engine Mount ..1301M28G06 71-00-00-90A-515 (1) RE 3/A

OR OR ..1301M28G07 (1) Platform, Engine Mount ..1301M28G06 71-00-00-90A-515 (1) RE 3/A

OR OR ..1301M28G06 * (S/B 72-222) (1) Platform, Engine Mount ..1301M28G06 71-00-00-90A-515 (1) RW 3/-

OR OR ..1301M28G04 * (S/B 72-222) (1) Platform, Engine Mount ..1301M28G04 71-00-00-90A-515 (1) RW 3/-

OR OR ...1301M28G05 * (S/B 72-222) (1) Platform, Engine Mount ..1301M28G05 71-00-00-90A-515 (1) RW 3/-
...1380M32P17 (2) Bushing, Flanged (Bottom) ...9383M49P10 71-00-00-90A-522 (2) RE 3/A
------- (-) Bushing, Flanged ...9383M49P23 71-00-00-90A-522 (AR) DE 5/A
------- (-) Bushing, Flanged ...9383M49P24 71-00-00-90A-522 (AR) DE 5/A
------- (-) Bushing, Flanged ...9383M49P25 71-00-00-90A-522 (AR) DE 5/A

.683L163G02 (X) Kit, Front Mount Platform (CF6-80C2B/BF) .683L163G02 (X) RM -/-

..1292M13G06 (1) Platform, Engine Mount ..1292M13G04 71-00-00-90A-515 (1) RE 3/A

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 17 New Part Number Qty/ Eng Part Name Old Part Number/ IPC Location Qty/ Eng Op Code Chg/ Sprt Code

..1292M13G05 (1) Platform, Engine Mount ..1292M13G04 71-00-00-90A-515 (1) RE 3/A

..1292M13G06 (1) Platform, Engine Mount ..1292M13G05 71-00-00-90A-515 (1) RE 3/A

OR OR ..1292M13G04 * (S/B 72-222) (1) Platform, Engine Mount ..1292M13G04 71-00-00-90A-515 (1) RW 3/-

OR OR ..1292M13G03 * (S/B 72-222) (1) Platform, Engine Mount ..1292M13G03 71-00-00-90A-515 (1) RW 3/-
...1380M32P17 (2) Bushing, Flanged (Bottom) ...9383M49P10 ** 71-00-00-90A-522 (2) RE 3/A
------- (-) Bushing, Flanged ...9383M49P23 ** 71-00-00-90A-522 (AR) DE 5/A
------- (-) Bushing, Flanged ...9383M49P24 ** 71-00-00-90A-522 (AR) DE 5/A
------- (-) Bushing, Flanged ...9383M49P25 ** 71-00-00-90A-522 (AR) DE 5/A

OR OR ..1292M13G06 (1) Platform, Engine Mount ..1292M13G05 71-00-00-90A-515 (1) RW 3/A
...1380M32P17 (2) Bushing, Flanged ...1380M32P04 71-00-00-90A-550 (2) RE 3/A * Denotes parts reworked in field and reidentified by adding Service Bulletin number adjacent to

part number. ** Old part not in the CF6-80C2BF IPC, new part number is in CF6-80C2BF IPC.

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 18 Change Codes 3 = Not interchangeable. 5 = Qualified interchangeability - parts added/deleted Spare Parts Support Code A = Old parts will no longer be supplied. Operation Codes RM = Remains RE = Replace RW = Rework DE = Delete AD = Add D. Parts Disposition Rework old fan frame, yoke, and platform. Use all other old parts to support unmodified engines provided life limits are not exceeded. E. Tooling - Price and Availability Special rework tool kits listed below are needed to accomplish the rework portion of this Service Bulletin: Tool Number Description ACSC2413 AI Platform Holding Fixture ACSC2414 TBC Platform Holding Fixture ACSC2415 Yoke Rework/Holding Fixture ACSC2447 Fan Frame Rework Fixture The rework tool kits required to accomplish this Service Bulletin will be provided by GE Aircraft Engines on and allocated basis. Submit a No-Charge Purchase Order making reference to CF6-80C2 S/B 72-222 to: GE Aircraft Engines Attn: Manager, Commercial Tooling Mail Drop IB10 10083 International Blvd. Cincinnati, OH 45246-4845, USA

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 19 3. ACCOMPLISHMENT INSTRUCTIONS A. Remove and disassemble the forward engine mount assembly per Section 72-00-01, DISASSEMBLY, of the referenced Engine Manual. Discard removed nuts J626P05. B. Inspect the forward engine mount assembly per the CF6-80C2 Engine Manual, 72-23-10, INSPECTION. C. Rework the Forward Engine Mount Platform as Follows: (1) Remove bushings from clevis bores of platforms 1301M28G06 (Airbus) or 1292M13G04 (Boeing). (2) Install appropriate platform holding fixture, ACSC2413 (Airbus) or ACSC2414 (Boeing), onto a jig bore machine. (3) Install platform into fixture as shown in figure 1 and secure with bolts. Check for gaps between fixture and platform along surface E with a 0.002 inch (0,05 mm) shim. (4) Adjust jack screws to support platform and align existing bores with spindle of Jig bore machine per requirements of figure 1. (5) Clamp platform with strap clamps and re-check alignment and spindle concentricity per figure 1. (6) Using standard boring head and carbide insert boring bar, set boring bar to existing bore diameter. (7) Bore a 1.2390-1.2395 inch (31,470-31,483 mm) diameter hole through both bores of each clevis. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. See figure 2. (8) Bore a 1.2405-1.2410 inch (31,509-31,521 mm) diameter hole through the top lug hole only on each clevis. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (9) Counterbore a 1.54-1.58 inch (39,12-40,13 mm) diameter on the top clevis holes meeting dimension of 0.618-0.638 inch (15,70-16,20 mm). Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK.

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 20 (10) Using a 90-degree straight shank boring bar machine, counterbore a 1.54-1.58 inch (39,12-40,13 mm) diameter on the bottom clevis holes meeting the 2.263-2.273 inch (57,49-57,73 mm) dimension as illustrated in figure 2. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (11) Using a 45-degree straight shank boring bar, set bar to bore diameter and countersink a 1.30-1.32 inch (33,0-33,5 mm) diameter on both bores of each clevis. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (12) Machine clevis slot of engine mount platform 1301M28G06 as follows: NOTE: This procedure not required on engine mount platform 1292M13G04. (a) Remove clamps on either side securing platform to holding fixture ACSC 2413. Locally-manufacture a hold-down plate to secure the center of the platform to the holding fixture. (b) Using a vertical mill or jig-bore indicate spindle to align with platform clevis borewithin 0.003 inch (0,07 mm). Align both clevis bores to establish datum -Gperpendicular to datum -F-. See figure 3. (c) Re-align spindle with one of the clevis bores. Move table 3.50 inches (88.9 mm) outward in X direction and zero machine. Move table to clear spindle to install the 10.0 inch x 1 x 1.5 H.S.S. stagger tooth cutter. Return to zero table position. (d) Align cutter wheel with existing 1.0 inch (25.4 mm) slot and mill clevis slot in Y direction 0.99-1.01 Inch (25,2-25,6 mm) from datum -G- per figure 3. (e) Repeat machining for the other clevis. (f) Inspect machined area for the 0.99-1.01 inch (25,2-25,6 mm) slot dimension and 0.180-0.200 inch (4,57-5,08) radii and 0.618 inch (15,70 mm) minimum clevis thickness per figure 3, view A-A. (13) Break all sharp edges. Refer to the Commercial Engine Standard Practices Manual, 70-42-00, BLENDING PROCEDURES and 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (14) Fluorescent-penetrant inspect the machined area per 70-32-03 and to the limits of 70-32-02 of the referenced Commercial Engine Standard Practices Manual.

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 21 WARNING: WEAR THERMAL GLOVES AT ALL TIMES WHEN HANDLING CHILLED PARTS. (15) Coat bottom clevis lug hole with anti-seize compound (C02-060). Freeze new flanged bushings 1380M32P17 in dry Ice for 30 minutes. Press in new flanged bushing 1380M32P17 into the bottom lugs of each clevis. D. Field Rework of Forward Engine Mount Platform 1292M13G05 to 1292M13G06 as follows: (1) Remove flanged bushing 1380M32P04 and replace with flanged bushing 1380M32P17. Refer to CMM, 71-21-01, Repair 1. (2) Mark the part to a depth of 0.001-0.006 inch (0,03-0,15 mm). Refer to the Commercial Engine Standard Practices Manual, 70-16-04, VIBRO-PEEN MARKING. (a) Make a line through part number 1292M13G05. Make sure you can read the number. (b) Write the new number 1292M13G06 on the part. E. Rework Yoke Assembly as follows: (1) Using dykem, mark the yoke with top lug and bottom lug as shown in figure 5. (2) Remove bottom lug bushings from the fan frame link and platform link attachment holes. NOTE: New yokes 9383M43G13/G14 have pressed-in bushings on top lug holes and do not require rework. (3) Mount holding fixture ACSC2415 onto jig bore machine. (4) Load yoke into holding fixture as in figure 4. Indicate bores to be in alignment and centered with spindle within 0.001 inch (0,025 mm). NOTE: Yoke is inverted from its normal engine orientation when installed in the holding fixture. (5) Using standard boring head and carbide insert boring bar, set boring bar to existing platform link attachment bore diameter. See figure 5, section K-K.

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 22 (6) Bore a 1.2390-1.2395 inch (31,470-31,483 mm) diameter through both platform link attachment bores. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (7) Bore a 1.2405-1.2410 inch (31,509-31,521 mm) diameter through the lug marked top lug only. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (8) Using a 90-degree straight shank boring bar machine counterbore a 1.54-1.58 inch (39,12-40,13 mm) diameter in the lug marked bottom lug, meeting the 0.523-0.533 inch (13,29-13,53 mm) dimension in figure 5, section K-K, and having a 0.04-0.06 inch (1,0-1,5 mm) fillet radius at the bottom of the counterbore. Ensure clean-up of existing counterbore. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (9) Counterbore a 1.54-1.58 inch (39,12-40,13 mm) diameter in the lug marked top lug clevis hole, meeting the 2.021-2.041 (51,34-51,83 mm) dimension illustrated in figure 5, section K-K, and having a 0.04-0.06 inch (1,1-1,5 mm) fillet radius at the bottom of the counterbore. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. Ensure clean-up of existing counterbore. (10) Using a 45-degree straight shank boring bar, set bar to bore diameter and countersink a 1.30-1.32 inch (33,0-33,52 mm) diameter on both bores of each clevis. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (11) Using standard boring head and carbide insert boring bar, set boring bar to existing fan frame link attachment bore diameter. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. See figure 5, section J-J. (12) Bore a 1.0840-1.0845 inch (27,534-27,546 mm) diameter through both fan frame link attachment bores. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (13) Bore a 1.0855-1.0860 inch (27,572-27,584 mm) diameter through the marked top lug only. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK.

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 23 (14) Using a 90-degree straight shank boring bar machine, counterbore a 1.41-1.45 inch (35,9-36,8 mm) diameter in the lug marked bottom lug bore, meeting the 0.523- 0.533 inch (13,9-13,53 mm) dimension illustrated in figure 5, section J-J, and having a 0.04-0.06 inch (1,0-1,5 mm) fillet radius at the bottom of the counterbore. Ensure clean-up of existing counterbore. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (15) Counterbore a 1.41-1.45 inch (35,9-36,8 mm) diameter in the lug marked top lug hole, meeting the 2.021-2.041 (51,34-51,83 mm) dimension illustrated in figure 5, section J-J, and having a 0.04-0.06 inch (1,0-1,5 mm) fillet radius at the bottom of the counterbore. Ensure clean-up of existing counterbore. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (16) Using a 45-degree straight shank boring bar, set bar to bore diameter and countersink a 1.15-1.17 inch (29,2-29,7 mm) diameter on both bores of each clevis. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (17) Remove yoke from holding fixture and reinstall to bore the other side link mounting holes. Repeat procedure for boring fan frame link and platform link attachment bores. (18) Break all sharp edges. Refer to the Commercial Engine Standard Practices Manual, 70-42-00, BLENDING PRACTICES, and 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. WARNING: WEAR THERMAL GLOVES AT ALL TIMES WHEN HANDLING CHILLED PARTS. (19) Coat bottom clevis hole with anti-seize compound (C02-060). Freeze flanged bushings 1380M32P15 and 1380M32P16 in dry Ice for 30 minutes. Press flanged bushings 1380M32P15 into bottom lugs of fan frame link attachment clevis and flanged bushings 1380M32P16 into bottom lug of platform link attachment clevis. (20) Remove bearing 9204M99P02 at fan frame attachment point. Install new bearing MS14101-12C and swage. Uniball must be free to rotate. NOTE: If hole diameter is oversize, select the correct size bearing as follows: PART NUMBER SIZE MS14101-12 or MS14101-12C 1.4370-1.4375 in. (36,500-36,513 mm) 1518M37P01 thru 1518M37P04 1.4375-1.4380 in. (36,513-36,525 mm)

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 24 PART NUMBER SIZE 1518M37P05 thru 1518M37P08 1.4420-1.4425 in. (36,627-36,639 mm) 1518M37P09 thru 1518M37P12 1.4470-1.4475 in. (36,754-36,766 mm) 1518M37P13 thru 1518M37P16 1.4475-1.4480 in. (36,767-36,779 mm) F. Rework the Fan Frame using Machining Fixture ACSC2447 as follows: (1) Remove bushings, thrust reverser ring and two upper acoustical panels. Refer to the CF6-80C2 Engine Manual, 72-23-00, DISASSEMBLY. (2) Inspect bores of fan frame clevises for fretting. Report any sign of fretting to the local GE Aircraft Engines representative. See figure 6. (3) Place two holes of fixture over studs on the aft side of the fan frame just below one of the fan frame clevises. (4) Slide alignment bar through large diameter in fixture, through both bores of clevis and through opposite end of fixture. See figure 7. (5) Using jack screws, nuts, and bolts of fixture, tighten fixture. Ensure free movement of alignment bar. (6) Slide carbide insert boring bar through fixture. Slide pinion over bar and engage rack. Attach air tool to boring bar and secure with set screw. (7) Rough-bore holes by feeding boring bar (M-5349D64) into clevis bore using the pinion gear. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. Back boring bar out of bore frequently to relieve chips. Feed smoothly and steadily. Rough-bore four times with the inserts set as follows. See figure 8. Rough Bore Dimension A First Bore: 0.950 inch (24,13 mm) Second Bore: 0.970 inch (24,64 mm) Third Bore: 0.990 inch (25,15 mm) Fourth Bore 1.005 inch (25,53 mm) NOTE: Dimension A is used to set size of boring bar. Hole size actually machined is larger than dimension A.

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 25 (8) Install reamer (M-5349D69) and ream both bores to a diameter of 1.0840-1.0845 inch (27,534-27,546 mm). Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (9) Install reamer (M-5349D68) and ream both bores to a diameter of 1.0855-1.0860 inch (27,572-27,584 mm). Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. NOTE: Fool proof sleeve must be removed from reamer (M-5349D68) to ream through both bores. (10) Install countersink bar (M-5349D65) and run down until insert touches top lug bore. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. Start air tool and feed bar down 0.032-0.042 inch (0,82-1,06 mm). (11) Remove countersink bar and boring fixture ACSC2447 from fan frame clevis. (12) Using a right-angle air drill and a 1.250 inch (31,75 mm) diameter abrasive stone (see figure 9), countersink the bottom lug bore to 1.15-1.17 inch (29,2-29,7 mm) diameter (80-120 degrees). Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. (13) Repeat boring procedure for the other fan frame clevis. (14) Remove all burrs and sharp edges from clevis bores. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK. Clean chips and cutting oil from fan frame. (15) Inspect bore diameters and countersinks. WARNING: WEAR THERMAL GLOVES AT ALL TIMES WHEN HANDLING CHILLED PARTS. (16) Coat bottom lugs of each clevis with anti-seize compound (C02-060). Freeze new flanged bushing 1380M32P10 in dry Ice for 30 minutes. Press flanged bushings 1380M32P10 into bottom lugs of each of the fan frame clevises. NOTE: A 0.8750 inch (22,225 mm) diameter pin must pass thru bushing after installation. If pin does not pass thru bushing, install flange bushing 1380M32P11 into top clevis hole to use for alignment and ream the lower bushing to 0.8755 in (22,237 mm) diameter maximum. Refer to the Commercial Engine Standard Practices Manual, 70-42-02, REPAIR PRACTICES FOR HOLE REWORK.

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 26 CAUTION: INSPECT PART NUMBERS OF FAN FRAME BEARINGS AT THE YOKE ATTACHMENT POINTS. ONLY BEARINGS 9204M99P01/P02/P03/P04 ARE TO BE REPLACED. (17) Remove two bearings 9204M99P01/P02/P03/P04 from the fan frame at the yoke attachment points. Install two new bearings MS14101-12C and swage. Uniball must be free to rotate. See figure 6. NOTE: If hole diameter is oversize, select the correct size bearing as follows: PART NUMBER SIZE MS14101-12 or MS14101-12C 1.4370-1.4375 in. (36,500-36,513 mm) 1518M37P01 thru 1518M37P04 1.4375-1.4380 in. (36,513-36,525 mm) 1518M37P05 thru 1518M37P08 1.4420-1.4425 in. (36,627-36,639 mm) 1518M37P09 thru 1518M37P12 1.4470-1.4475 in. (36,754-36,766 mm) 1518M37P13 thru 1518M37P16 1.4475-1.4480 in. (36,767-36,779 mm) G. Reidentify yoke assembly 9383M43G01, yoke 9383M41P01, fan frame 9382M46/48, and engine mount platform assembly 1301M28G04/G05/G06 (CF6-80C2A Series) or 1292M13G03/G04 (CF6-80C2B Series) by marking SB 72-222 adjacent to the part number, using the shallow vibropeen method of marking to a depth of 0.001-0.006 inch (0,03-0,15mm) per chapter 70-16-04 of the referenced Commercial Engine Standard Practices Manual. Using the shallow vibropeen method of marking to a depth of 0.001-0.006 inch (0,03-0,15 mm) per chapter 70-16-04 of the referenced Commercial Engine Standard Practices Manual, line out the old part number, maintaining legibility, and reidentify the fan frame as follows: Old Part Number Reidentify To

9382M37G47 9382M37G53 H. Assemble the forward engine mount assembly. Refer to the CF6-80C2 Engine Manual, 72-00-01, ASSEMBLY using reworked/new hardware and new nuts J626P05. NOTE: If new yoke assembly 9383M43G13/G14 is used, the top lugs of the link attachment points have pressed-in bushings (IPC 72-00-00-45-200/205) and the bottom lugs have slip-fit bushings (IPC 72-00-00-45-240/340/410/510).

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# CF6-80C2
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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 27 Platform/Holding Fixture Setup (TBC Shown) Figure 1

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 28 Platform Machining Information (AI Shown) Figure 2

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 29 Machining Information for AI Platform Link Clevises Figure 3

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 30 Machining Setup for Yoke Figure 4, Sheet 1

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 31 Machining Setup for Yoke Figure 4, Sheet 2

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 32 Yoke Machining Information Figure 5

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 33 Fan Frame Clevis Mounts Figure 6, Sheet 1

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 34 Fan Frame Clevis Mounts Figure 6, Sheet 2

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 35 Fan Frame Rework Fixture, ACSC2447 Figure 7

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 36 Boring Bar Tool, M-5349D64 Figure 8

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# SERVICE BULLETIN ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222 Revision 4, February 29, 2000 Page 37 Fan Frame Clevis Countersink Figure 9