̇ 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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 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.
 ̇ 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
 ̇ 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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 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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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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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.
 ̇ 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
 ̇ 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
 ̇ 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
 ̇ 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
 ̇ CF6-80C2

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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/-
 ̇ CF6-80C2

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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
 ̇ 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/-
 ̇ 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 -/-
 ̇ 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
 ̇ 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.
 ̇ CF6-80C2

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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
 ̇ CF6-80C2

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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.
 ̇ CF6-80C2

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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 bore

within 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.
 ̇ 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 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.
 ̇ CF6-80C2

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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.
 ̇ CF6-80C2

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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)
 ̇ CF6-80C2

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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.
 ̇ CF6-80C2

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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.
 ̇ CF6-80C2

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

April 26/88 CF6-80C2 S/B 72-0222

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Machining Information for AI Platform Link Clevises

Figure 3
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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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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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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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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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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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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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ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

April 26/88 CF6-80C2 S/B 72-0222

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Boring Bar Tool, M-5349D64

Figure 8
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ENGINE - Assembly (72-00-00) - Redesigned Forward Engine Mount System

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Fan Frame Clevis Countersink

Figure 9